RESULTS OF THE SECOND
U.S. MANNED
SUBORBITAL SPACE FLIGHT
JULY 21, 1961
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FOREWORD
This document presents the results of the second United States manned suborbital
space flight. The data and flight description presented form a continuation of the
information provided at an open conference held under the auspices of the National
Aeronautics and Space Administration, in cooperation with the National Institutes of
Health and the National Academy of Sciences, at the U.S. Department of State Audi-
torium on June 6, 1961. The papers presented herein generally parallel the presenta-
tions of the first report and were prepared by the personnel of the NASA Manned
Spacecraft Center in collaboration with personnel from other government agencies,
participating industry, and universities.
CONTENTS
FOREWORD iii
1. INTRODUCTION 1
By Robert R. Gilruth, Director, NASA Manned Spacecraft Center.
2. SPACECRAFT AND FLIGHT PLAN FOR THE MERCURY- REDSTONE 4
FLIGHT 3
By Jeror je B. Haminack, Mercury-Redstone Project Engineer, .N ASA Manned
Spacecraft Center.
3. RESULTS OF THE MR 4 PRE FLIGHT AND POSTFL1GHT MEDICAL EXAMI-
NATION CONDUCTED ON ASTRONAUT VIRGIL I. GRISSOM 9
By William K. Douglas, M.D., Astronaut Flight Surgeon, NASA Manned Space-
craft Center; Carmault B. Jackson, Jr., M.D., Life Systems Division, NASA
Manned Spacecraft Center: Ashton Graybiel, M.D., USN School of Aviation Medi-
cine, Pensacola, Fla.: George Ruff, M.D., University of Pennsylvania; Edward C.
Knoblcck, Ph. D., Walter Reed Army Medical Center; William S. Angerson, M.D.,
Life Systems Division, NASA Manned Spacecraft Center; and C. Patrick Laugh-
lin, M.D., Life Systems Division, N ASA Manned Spacecraft Center.
4. PHYSIOLOGICAL RESPONSES OF THE ASTRONAUT IN THE MR 4 SPACE
FLIGHT 15
By C. Patrick Laughlin, M.D., Life Systems Division, NASA Manned Spacecraft
Center and William S. Augerson, M.D., Life Systems Division, NASA Manned
Spacecraft Center.
.). FLIGHT SURGEON'S REPORT FOR MERCURY-REDSTONE MISSIONS 3 AM)
4 23
By William K. Douglas, M.D., Astronaut Fight Surge' n, NASA Manned Space-
craft Center.
6. RESULTS OF INFLIGHT PILOT PERFORMANCE STUDIED FOR THE MR I
FLTGHT 33
By Robeit B. Voas, Ph. D., Head, Training Office, NASA Manned Spacecraft Center;
John J. Van Bockel, Training Office, NASA Manned Spacecraft Center: Raymond
G. ZedeVar, Training Office, NASA Manned Spacscraft Center: and Paul W.
Hacker. McDonnell Aircraft Corp.
7. PILOT'S FLIGHT REPORT 47
By \ irgil I. Grissom, Astronaut, NASA Manned Spacecraft Center.
iv
1. INTRODUCTION
By Robert R. Gilruth, Director. NASA Manned Spacecraft Center
The second successful manned suborbital space
flight on July 21, 1961, in which Astronaut Virgil 1.
Grissom was the pilot was another step in the
progressive research, development, and training
program leading to the study of man's capabilities
in a space environment during manned orbital flight.
Data and operational experiences gained from this
flight were in agreement with and supplemented the
knowledge obtained from the first suborbital flight
of May 5, 1961, piloted by Astronaut Alan B.
S: ~ d, Jr.
wo recent manned suborbital flights, coupled
wiUi ine unmanned research and development flights,
have provided valuable engineering and scientific
data on which the program can progress. The suc-
cessful active participation of the pilots, in much
the same way as in the development and testing of
high performance aircraft, has greatly increased our
confidence in giving man a significant role in future
space flight activities.
It is the purpose of this report to continue the
practice of providing data to the scientific com-
munity interested in activities of this nature. Brief
descriptions are presented of the Project Mercury
spacecraft and flight plan. Papers are provided
which parallel the presentations of data published
for the first suborbital space flight. Additional
information is given relating to the operational
aspects of the medical support activities for the two
manned suborbital space flights.
1
2. SPACECRAFT AND FLIGHT PLAN FOR
THE MERCURY-REDSTONE 4 FLIGHT
By Jerome B. HamMACK, Mercury-Redstone Project Engineer, NASA Manned Spacecraft Center
Introduction
The Mercury spacecraft is described in some de-
tail in references 1 and 2. The MPH flight was
the fourth mission in the Mercury-Redstone series
of flight tests, all of which utilized the Mercury
spacecraft. Each spacecraft differed in small de-
tails, and the differences between the MR-3 and the
MR-4 spacecraft are discussed herein.
As shown in figure 2-1, the main configuration
differences were the addition to the MR-4 space-
craft of a large viewing window and an explosively
actuated side hatch.
Window
The addition of the large viewing window in the
position shown in the figure was a result of a change
requested by the Mercury astronauts. This window
enables the astronaut to have a greater viewing area
than the original side port windows. The field of
view of the window is 30° in the horizontal plane
and 33° in the vertical.
HATCH EXPLOSIVE IGNITER
^ (MR-4)
HATCH EXTERNAL
rfXPLOSIVE CONTROL
(MR-4) ;
ENTRANCE HATCH
INTERNAL RELEASE
HANDLE (MR-3)
EXTERNAL RELEASE
HANDLE SOCKET
(MR-3)
ENTRANCE HATCH
LOWER WINDOW
(MR-3)
RSCS RATE DAMPER BOX
(MR-4)
EXTERNAL RELEASE HANDLE
(STOWED POSITION)
(MR-3) —
UPPER WINDOW
(MR-3)
MR-4 WINDOW
HATCH INTERNAL
EXPLOSIVE CONTROL
(MR-4)
- CABIN AIR
INLET VALVE
. (MR-4)
CABIN AIR INLET VALVE
(MR-3)
Figure 2-1. Configuration differences between MR-3 and MR-4 spacecraft.
3
The window is composed of an outer panel of
0.35-inch-thick Vycor glass and a 3-layer inner
panel. The top layer of this inner panel is 0.17-inch-
thick Vycor glass and the other two layers are 0.34-
inch-thick tempered glass. The Vycor glass panels
will withstand temperat ares in the range of 1,500°
to 1.800° F. The inner layers of tempered glass
will withstand the cabin-pressure differences. Mag-
nesium fluoride coatings were applied to reduce
glare. Although not installed for the MR-4 flight,
a removable polaroid filter to reduce glare further
and a red filter for night adaption are available for
the window .
Side Hatch
The explosively actuated side hatch was used for
the first time on the MR-4 flight. The mechanically
operated side hatch on :he MR-3 spacecraft was in
the same location and o : the same size, but was con-
siderably heavier (69 pounds as installed rather
than 23 pounds) .
The explosively actuated hatch utilizes an ex-
plosive charge to fracture the attaching bolts and
thus separate the hatch from the spacecraft. Seventy
Vi-inch titanium bolts secure the hatch to the door-
sill. A 0.06-inch-diameter hole is drilled in each
bolt to provide a weak point. A mild detonating
fuse ( MDF I is installed in a channel between an
inner and outer seal around the periphery of the
hatch. When the MDF is ignited, the resulting gas
pressure between the inner and outer seal causes
the bolts to fail in tension.
The MDF is ignited by a manually operated ig-
niter that requires an actuation force of around 5
pounds, after removal of a safety pin. The igniter
can be operated externally by an attached lanyard,
in which case a force jf at least 40 pounds is re-
quired in order to shear the safety pin.
Other differences be:ween the MR-3 spacecraft
and the MR-4 spacecraft, not visible in figure 2-1,
include: (a I redesigned clamp-ring covers, (b)
changed instrument paiel, and (c) the incorpora-
tion of a rate command control system.
Clamp-Ring Covers
The fairings around the explosive bolts were
changed to a more streamlined shape from the orig-
inal rectangular shape to reduce buffeting. Also, the
upper part of the fairings were hinged so that at
separation they would flip off rather than slide
dow7n. There was evidence that on a previous Little
Joe-Mercury flight, the umbilical connections had
MR-4
Figure 2-2. Clamp-ring covers for MR-3 and MR-4
spacecraft.
been damaged by this sliding action. Figure 2-2
shows the differences between the MR-3 and MR^l
covers.
Instrument Panel
A comparison between the MR4 spacecraft in-
strument panel, shown in figure 2-3, and the MR-3
panel, presented in reference 1, reveals that the dif-
ferences were mainly the rearrangement of controls
and indicators and the addition of an earth-path
indicator. The earth-path indicator was inoperative
for the MR— 4 flight, however.
Rate Stabilization and Control Systen.
The major difference between the stabilization
and control systems of the MR— 3 and MR-4 space-
craft was the addition to the MR— 4 spacecraft of a
rate command control system which operated in
connection with the manual reaction control system.
The rate stabilization and control system (RSCS)
senses and commands spacecraft rates rather than
attitudes. The system damps to the commanded
rate to within +3 deg/sec. Without manual com-
mand, it damps to zero rate within ±3 deg/sec.
Prelaunch Preparations
The prelaunch preparation period was essentially
the same as for the MR— 3 mission. A brief descrip-
tion of the activity during this period follows.
Astronaut
Prior to launch of the MR^l spacecraft, the as-
signed pilot for the mission started an intense train-
ing routine at Cape Canaveral, Fla., and at the
NASA Manned Spacecraft Center, Langlev *ir
4
Figure 2-3. Main instrument panel and consoles for MR-4 spacecraft.
Force Base, Va., to familiarize himself with the
various details of the spacecraft systems and to
sharpen his reactions to various situations. During
this period, the pilot participated in a centrifuge
training program in which 17 Mercury acceleration
profiles were run. The pilot took part in environ-
ir control system tests, communication tests,
r control system tests; obtained 100 simu-
lateu missions on the procedures trainer: conducted
36 simulated missions on the air-lubricated free-
attitude (ALFA) trainer; and practiced insertion
exercises and R.F tests in which the pilot and space-
craft were exercised in a simulated count through
lift off. On July 21, 1961, after two delays in the
launch date, the pilot was prepared and inserted in
the spacecraft at 3:58 a.m. e.s.t. Launch occurred
at 7:20 a.m. e.s.t.
Mercury Control Center
The Mercury Control Center provided excellent
support for the MR^l mission. Numerous simu-
lated flights were run prior to launching which uti-
lized the flight astronauts in the procedures trainer
and the personnel of the flight control center and
network.
Spacecraft
The spacecraft was delivered to Hangar "S" at
Cape Canaveral, Fla., on March 7, 1961. Upon de-
livery, the instrumentation and selected items of
t> imunication system were removed from the
spacecraft for bench testing. After reinstallation of
the components, the systems tests proceeded as
scheduled with only slight interruptions for work
periods. Those tests required a total of 33 days,
during which the electrical, sequential, instrumenta-
tion, communication, environmental, reaction-con-
trol, and stabilization and control systems were
individually tested. After systems tests, a short
work period was required to install the landing-im-
pact bag. A simulated flight was then run on the
spacecraft which was followed by installation of
parachutes and pyrotechnics, weighed and balanced,
and delivered to the launch complex for mating with
the booster. Twenty-one days were spent on the
launching pad during which the spacecraft and
booster systems were checked both separately and
as a unit. After the systems checks were completed,
a spacecraft — launch-vehicle simulated flight was
performed. The spacecraft — launch-vehicle com-
bination was then ready for launch. A period of
136 days elapsed between delivery of the spacecraft
to Cape Canaveral, Fla., and its successful launch.
The MR-4, launch occurred on July 21, 1961, 47
days after the first manned ballistic flight bv Astro-
naut Alan B. Shepard, Jr.
Launch Vehicle
The launch-vehicle system checks and prepara-
tions proceeded as scheduled with only minor mal-
functions which caused no delays in the schedule.
During the split countdown on the launching pad,
5
the launch-vehicle countdown proceeded smoothly
with no hold periods chargeable to the launch-vehicle
systems.
Countdown
The MR-4 spacecraft was launched at 7:20 a.m.
e.s.t. on July 21, 1961 (fig. 2-4). The launch was
originally scheduled for July 18. 1961, but was
rescheduled to July 19, 1961, because of unfavorable
weather conditions. The launch attempt of July 19.
Figure 2-4. Launch of the Mercury-Redstone 4 from Cape
Canaveral launch site on July 21, 1961.
1961, was canceled at T— 10 minutes as a result of
continued unfavorable weather. The launch was
then rescheduled for July 21, 1961. The first half
of the split launch countdown was begun at 6 :00 a.m.
e.s.t. on July 20. 1961. at T — 640 minutes. Space-
craft preparation proceeded normally through the
12-hour planned hold period for hydrogen peroxide
and pyrotechnic servicing. Evaluation of the
weather at this time affirmed favorable launch condi-
tions. The second halt of the countdown was there-
fore begun at 2:30 a.m. e.s.t. on July 20. 1961. At
T— 180 minutes, prior to adding liquid oxygen to
the launch vehicle, a planned 1-hour hold was called
for another weather evaluation. The weather
evaluation was favorable and the countdown pro-
ceeded from T— 180 minutes at 3:00 a.m. e.s.t. No
further delays in the countdown were encoi'^+ered
until T — 45 minutes. A 30-minute hold w ;d
at this time to install a misalined hatch L At
T — 30 minutes, a 9-minute hold was required to turn
off the pad searchlights which interfere with launch-
vehicle telemetry during launch. At T— 15 minutes,
a 41-minute hold was required to await better cloud
conditions. The count then proceeded from T— 15
until lift-off.
The pilot was in the spacecraft 3 hours and 22
minutes prior to launch.
Flight Description
The MR-4- flight plan was very much the same as
that for the MR-3. The flight profile is shown in
figure 2-5. As shown, the range was 262.5 nautical
miles, the maximum altitude was 102.8 nautical
miles, and the period of weightlessness lasted for
approximately 5 minutes.
The sequence of events was as follows :
At T — 35 seconds, the spacecraft umbilical was
pulled and the periscope was retracted. During
the boosted phase of flight, the flight-path angle was
controlled bv the launch-vehicle control system.
Launch-vehicle cutoff occurred at T + 2 minutes 23
seconds, at which time the escape tower clamp ring
was released, and escape tower was rele. '-d_ by
firing the escape and tower jettison rocke' m
seconds later, the spacecraft-to-launcl ie
adapter clamp ring was separated, and the posi grade
rockets fired to separate the spacecraft from the
launch vehicle. The periscope was extended; the
automatic stabilization and control system provided
5 seconds of rate damping, followed bv spacecraft
turnaround. It then oriented the spacecraft to orbit
attitude of —34°.
Retrosequence was initiated by timer at T + 4
minutes 46 seconds, which was 30 seconds prior to
the spacecraft reaching its apogee.
The astronaut assumed control of spacecraft atti-
tude at T + 3 minutes 5 seconds and controlled the
spacecraft by the manual proportional control system
to T + 5 minutes 43 seconds. He initiated firing of
the retrorockets at T — 5 minutes 10 seconds. From
T— 5 minutes 43 seconds, he controlled the space-
craft by the manual rate command system through
reentry. The retrorocket package was jettisoned at
T + 6 minutes 7 seconds. The drogue parachute
was deployed at T + 9 minutes 41 seconds, and main
parachute, at T+10 minutes 14 seconds. Landing
occurred at T— 15 minutes 37 seconds.
6
TIKE REFERENCE - MIN:SEC
A comparison of the flight parameters of MR-4
and MR-3 spacecraft, listed in table 2-1, shows that
both flights provided similar conditions.
Figure 2-5. Flight profile for MrM.
ACCELERATION,
q UNITS
I2r
Table 2-1. — Comparison of Flight Parameters for
MR-3 and MR-4 Spacecraft
_ Parameter
MR 3
MR-4
flight
flight
263. 1
262.5
Maximum altitude, nautical miles. .
101. 2
102.8
Maximum exit dynamic pressure,
lb/sq ft
586. 0
605.5
Maximum exit longitudinal load
6.3
6.3
Maximum reentry longitudinal
11.0
11. 1
Period of weightlessness, min:sec . .
5:04
5:00
6,414
6,618
Space-fixed velocity, ft /sec
7,388
7,580
The acceleration time history occurring during the
MR-4 flight is shown in figure 2—6 and is very sim-
ilar to that of the MR-3 flight fref. 1).
The recovery-force deployment and spacecraft
landing point are shown in figure 2-7. The space-
craft was lost during the postlanding recovery period
as a result of premature actuation of the explosively
actuated side egress hatch. The astronaut egressed
from the spacecraft immediately after hatch actua-
tion and was retrieved after being in the water for
alv>"f 3 to 4 minutes.
10
8
6
4
2
,-LAUNCH-
\ VEHICLE
\ CUTOFF
2MIN, 23 SEC
^
REENTRY
^ETROFIRE
' Ai A
T-MAIN PARACHUTE
DEPLOYMENT
J
0 2 4 6 8 10 12 14
TIME, MIN
Figure 2-6. Acceleration time history for MR^ flight.
The spacecraft and its systems performed well on
the MR-4 flight: the major difficulty was the as yet
unexplained premature separation of the side egress
hatch. A minor control problem was noted in that,
design turning rates were not achieved with full stick
deflection. This problem is believed to be due to
control linkage rigging.
SPACECRAFT
"TTIHI LANDING
POINT
Figure 2-7. Chart of recovery operations.
7
References
1. Anon.: Proceedings oj Conference on Results oj the First U.S. Manned Suborbital Space Flight. NASA, ,t.
Health, and Nat. Acad Sci., June 6. 1961.
2. Hammack, Jerome B., End Heberlic, Jack C: The Mercury-Redstone Program. | Preprint] 2238-61. American Kocket
Soc., Oct. 1961.
8
RESULTS OF THE MR-4 PREFLIGHT AND POSTFLIGHT
MEuICAL EXAMINATION CONDUCTED ON ASTRONAUT VIRGIL
I. GRISSOM
By William K. Douglas, M.D., Astronaut Flight Surgeon, NASA Manned Spacecraft Center; Carmault
B. Jackson, Jr., M.D., Life Systems Division, NASA Manned Spacecraft Center; Ashton Graybiel,
M.D., USN School of Aviation Medicine, Pensacola, Fla.; George Ruff, M.D., University of Penn-
sylvania; Edward C. Knoblock, Ph. D., Walter Reed Army Medical Center; William S. Augerson,
M.D., Life Systems Division, NASA Manned Spacecraft Center; and C. Patrick Laughlin, M.D.,
Life Systems Division, NASA Manned Spacecraft Center
This paper presents the results of the clinical
and biochemical examinations conducted on Astro-
naut Virgil I. Grissom prior to and following
the MR^l mission. The objectives of such an
examination program were presented in the MR-3
report on Astronaut Alan B, Shepard, Jr. (ref. 1).
Basically, the health of the astronaut before and
after the space flight was assessed and any altera-
tions were sought out that might have resulted from
the stresses imposed by the space flight. Similar
medical and biochemical examinations had been ac-
complished during the Mercury-Redstone centrifuge
training sessions and provided data of comparative
value.
J^-is important to point out the limitations in
< ing examination findings with specific flight
si a. The last preflight examination was per-
formed approximately 5 hours before lift-off and
the final postflight examination 3 hours after space-
craft landing. The strenuous effort by Astronaut
Grissom during his recovery from the ocean may
well have produced changes which overshadowed
any flight induced effects.
Astronaut Grissom was examined several times
in the preflight period as two launch attempts were
canceled before the actual flight on July 21, 1961.
The initial clinical and biochemical examinations
were performed on July 17, 1961, at which time
questioning disclosed no subjective complaints.
Positive physical findings were limited to shotty,
nontender inguinal and axillary adenopathy, and
mild pharyngeal lymphoid hyperplasia. The skin at
the lower sternal electrode placement site exhibited
a well circumscribed area (1 cm in diameter) of
eruption. This lesion appeared to consist of about
8 to 10 small pustules arising from hair follicles.
Upon closer examination of this eruption in August
1961, it became apparent that the pustules seen in
T id, by this later date, become inclusion cysts.
Culture of these lesions in August 1961 was sterile.
These lesions were attributed to the use of electrode
paste and were also noted on the pilot of MR-3
flight.
The preflight examination on July 21, 1961, is
reported in detail. A feeling of mild "sore throat"
was reported; otherwise the body systems review
was negative. Psychiatric examination reported "no
evidence of overt anxiety, that Astronaut Grissom
explained that he was aware of the dangers of flight,
but saw no gain in worrying about them." In fact,
"he felt somewhat tired, and was less concerned
about anxiety than about being sufficiently alert
to do a good job." At the physical examination
the vital signs ( table 3-1 ) were an oral temperature
of 97.8C F, blood pressure of 128/75 (right arm
sitting), weight of 150.5 lb, pulse rate of 68, and
respiration rate of 12. Inspection of the skin re-
vealed there were small pustules at the site of the
lower sternal electrode, but it was otherwise clear.
The same shotty nontender inguinal and axillary
nodes were felt. Eye, ear, nose, and mouth examina-
tion was negative. There was slight to moderate
oropharyngeal lymphoid hyperplasia. The trachea
was midline, the neck normally flexible, and the
thyroid gland unremarkable. The lungs were clear
to percussion and auscultation throughout. Heart
sounds were of normal quality, the rhythm was
regular, and the heart was not enlarged to percus-
sion. Palpitation of the abdomen revealed no
spasm, tenderness, or abnormal masses. The geni-
talia, back, and extremities were normal. Calf and
thigh measurements were:
Calf
Thigh
Right
Left
15% in. I 21 in.
15?/8 in. j. 20?4 in.
i
9
Neurological examination revealed no abnormality.
An electroencephalogram, electrocardiogram, and
chest X-ray were normal, unchanged from Septem-
ber 1960. Vital capacity standing, measured with
a bellows spirometer, was 5.0 liters. Analysis of
the urine and blood (tables 3-II and 3— III ) re-
vealed no abnormality.
As with the MR-3 flight, members of the medical
examining team were eilher transported to the Grand
Bahama Island debriefing site a day prior to launch
or flew down immediately after launch.
The initial postfligh: medical examination was
conducted immediately after Astronaut Grissom ar-
rived aboard the recovery aircraft carrier, USS
Randolph, approximately 15 minutes after space-
craft landing in the ocean. The examination was
conducted by the same physicians who examined
Astronaut Shepard aboard the USS Lake Champlain.
The findings disclosed vital signs of rectal tem-
perature of 100.4° F; pulse rate from 160 initially
to 104 (supine at end of examination) : blood pres-
sure of 120/85 LA sitting. 110/88 standing, and
118/82 supine: weight of 147.2 pounds, and respira-
tory rate of 28. On general inspection, the astro-
naut appeared tired and was breathing rapidly; his
skin was warm and moist. Eye, ear, nose, and
throat examination repealed slight edema of the
mucosa of the left nasal cavity and no other ab-
normalities. Chest examination showed no signs
of atelectasis although there was a high noise level
in the examining room. No rales were heard and
the pilot showed no tendency to cough. Vital ca-
pacity measured with a bellows spirometer while
still in suit was 4.5 liters.
Peripheral pulses were described as normal and
a left axillary node was noted. The abdomen was
soft with normal bowel sounds.
The pilot voided three times without fluid intake.
The limited neurological examination disclosed no
abnormalities. Extremity measurements were as
follows :
Calf Thigh
Right lSK in. ! 20Vi in.
Left 15K in. , 20% in.
After a short nap and breakfast he was flown to
Grand Bahama Island, arriving approximately 3
hours after spacecraft landing. His general appear-
ance was much improved. Vital signs were recorded
as a temperature of 98.4 (oral) ; blood pressure of
125/85 sitting. 124/82 standing, 122/78 ~e;
pulse rate of 90; and weight of 147.5 pound.
Ophthalmological examination approximately 6
hours postflight showed slight injection of the con-
junctiva of the left eye. These findings, as well as
nasal mucosa edema, were ascribed to salt water
exposure. The lungs remained clear to percussion
and auscultation. The abdomen, genitalia, back, and
extremities were normal. Neurological examination
revealed "changes consistent with muscular fatigue
in a normal individual." The electroencephalogram,
electrocardiogram, and chest X-ray revealed no
abnormality. Vital capacity measurement was 4.8
and 4.9 liters. An exercise tolerance test (Harvard
step) was within control range.
Additional examinations in the ensuing 48 hours
revealed no changes when compared with preflight
studies.
The vital signs are summarized in table 3-1. Re-
sults of the biochemical determination are presented
in tables 3— II to 3— V. Control data from Redstone
centrifuge experience are included.
Table 3-VI shows comparisons between clinical
observations from single simulated Redstone mis-
sions conducted at the Johnsville human centrifuge
I with a 5-psia 100-percent oxvgen environment) and
the MR— 4 flight. The examinations were m? 1 " be-
fore and after the simulation, at times compa :>
those in the actual flight.
An evaluation of the clinical and biochemical
studies permits the following conclusions:
(a) Astronaut Grissom was in good health prior
to and following his MR-4 flight. The immediate
postflight examination revealed changes consistent
with general fatigue and sea water exposure.
(b) Clinical examination disclosed no specific
functional derangement that could be attributed to
the spaceflight stresses.
(c) No specific biochemical alteration occurred
that could be attributed to a spaceflight stress effect.
Acknowledgments — Special acknowledgment is
paid to Drs. Robert C. Lanning fUSN) and Jerome
Strong (USA) who conducted the physical exami-
nation aboard the USS Randolph; Dr. James F.
Culver of the USAF School of Aviation Medicine,
who performed the ophthalmologic examinations;
Dr. Phillip Cox, Andrews Air Force Base Hospital,
who participated in the physical examinations ; and
Dr. Francis Kruse of the Lackland Air Force Base
Hospital, who performed the neurological exami-
nations. Dr. Walter Frajola of Ohio State I
10
sity made some of the biochemical determinations, Manned Spacecraft Center, collected and processed
ar Ns Rita Rapp, Life Systems Division, NASA the biochemical specimens.
Reference
1. Jackson, Carmault B., Jr., Douglas, William K., et al.: Results of Preflight and Postflight Medico! Examinations.
Proc. Conf. on Results of the First U.S. Manned Suborbital Space Flight, NASA, Nat. Inst. Health, and Nat. Acad. Sci.
June 6, 1961, pp. 31-36.
Bibliography
Glucose :
Nelson, M. : Photometric Adaptation of Somogyi Method for Determination of Glucose. Jour. Biol. Chem., vol. 153,
1944, pp. 375-380.
Total protein, albumin:
Cohn, C, and Wolfson, W. G. : Studies in Serum Proteins. I — The Chemical Estimation of Albumin and of the
Globulin Fractions in Serum. Jour. Lab. Clin. Med., vol. 32, 1947, pp. 1203-1207.
Gornall, A. G., Bahdawill, C. J., and David, M. M. : Determination of Serum Proteins by Means of the Biuret
Reaction. Jour. Biol. Chem., vol. 177, 1949, pp. 751-766.
Urea nitrogen:
Gentzkow, C. J., and Masen, J. M. : An Accurate Method for the Determination of Blood Urea Nitrogen by Direct
Nesslerization. Jour. Biol. Chem., vol. 143, 1942, pp. 531-544.
Calcium:
Diehl, H., and Ellincboe, J. L. : Indicator for Titration of Calcium in Presence of Magnesium With Disodium Dihy-
drogen Ethylene Diaminetetraacetate. Anal. Chem., vol. 28, 1956, pp. 882-884.
Chloride :
Schales, 0., and Schales, S. S. : A Simple and Accurate Method for the Determination of Chloride in Biological
Fluids. Jour. Biol. Chem., vol. 140, 1941, pp. 879-884.
Epinephrine and norepinephrine:
Weil-Malherbe, H., and Bone, A. D.: The Adrenergic Amines of Human Blood. Lancet, vol. 264, 1953, pp. 974^977.
Gray, I. Young, J. G., Keegan, J. F., Meheman, B., and Southerland, E. W. : Adrenaline and Norepinephrine Con-
centration, in Plasma of Humans and Rats. Clin. Chem., vol. 3, 1957, pp. 239-248.
Sodium potassium by flame photometry:
Bebkman S., Henhy, R. J., Golub, O. J., and Seagalove, M. : Tungstic Acid Precipitation of Blood Proteins. Jour.
" ^ol. Chem., vol. 206, 1954, pp. 937-943.
V ndelic acid:
derman. F. W„ Jr., et al.: A Method for the Determination of 3-Methoxy4-Hydroxymandelic Acid ("Vanil-
mandelic Acid") for the Diagnosis of Pheochromocytoma. Am. Jour. Clin. Pathol., vol. 34, 1960, pp. 293-312.
Table 3-1. — Vital Signs
Preflight
Postflight
-7 hr
(Cape Canaveral)
+ 30 min
(Shipboard)
Body weight nude (post voiding) j 150 lb 8 oz 147 lb 3 oz . .
Temperature, °F 97.8 (oral) 100.4 (rectal) .
Pulse per min 68 160 to 104.
28.
Respiration per min 12
Blood pressure, mm Hg: I
Sitting j 128/75 j 120/85.
Standing ! 110/88.
Supine j ; 118/82.
Vital capacity (bellows spirometer), liters. . . . 5.0 ; 4.5. . . .
+ 2 hr
(Grand Bahama
Island)
147 lb 8 oz
98.4 (oral)
90
14
125/85
124/82
122/78
4.8
4.9
11
Table 3— II. — -Results of Urine Tests
Centrifuge
MR-4 flight
Postrun
Preflight
Post flight
Pre-
run
During
+ 30
+ 2 hr
-6 hr
count-
+ 1 hr
+ 3 hr
+ 6 hr
+ 13 hr
+ 24 hr
min
down
hr 1
Sample volume, ml. . .
125
185
470
135
185
110
300
100
475
135
315
1. 023
1.005
1. 011
1.020
1.011
1. 010
1.022
1.020
1.022
1.025
1.015
Albumin
Neg.
Neg.
Neg,
Neg.
Neg.
Neg.
Neg.
Neg.
IN eg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Ketones
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
Neg.
pH
6.4
6.2
6.2
6.6
6.8
6.4
6. 0
6.0
6.0
6.0
6.8
130
28
79
142
76
70
122
128
140
114
140
K, mEq/L
62
28
39
35
18
19
37
39
25
49
71
CI, mEq/L
55
68
130
65
111
68
69
178
Microscopic examina-
tion
N
o formed element
s observed
Breakfast eaten follow ing previous sample.
Table 3— III. — Peripheral Blood Findings
Preflight
Postflight
— 3 days
+ 1 hr
+ 5 hr
+ 49 '
Hematocrit, percent
42.5
42.2
42.5
42. 7
Hemoglobin,1 g
14.1
14.4
14.6
14.2
White blood cells, per mm3
6,500
7, 200
9, 100
6, 700
Red blood cells, millions/mm'
4.81
4. 75
4. 67
4. 71
Differential blood count :
Lymphocytes, percent
46
40
29
35
Neutrophiles, percent
46
54
66
59
Band cells, percent
Monocytes, percent
5
4
3
4
1
2
2
2
Basophiles, percent
2
0
0
0
Acid Hematin met hoc*
12
Table 3-IV. — Blood Chemistry Findings
r
Sodium (serum), mEq/L. . .
Potassium (serum), mEq/L.
Chloride, mEq/L
Protein, total
Albumin, g/100 ml
Globulin, g; 100 ml
Glucose, mg/100 ml
Epinephrine,* Mg/L
Norepinephrine, 2 ^g/L
1 Normal values: 0. 0 to 0. 4 pglL
2 Normal values; 4. 0 to 8. 0 itgjh
Centrifuge
MR 4 flight
Postrun
Preflight
Postflight
Prerun
+ 30 min
+2 hr
— 4 days
+ 1 hr
+ 5 hr
+ 49 hr
147
141
143
142
140
144
141
5.4
5.9
4. 6
4. 1
3.5
4.4
4.8
89
94
90
97
95
101
99
7.5
8.0
7.6
7.4
7.3
7.1
7.9
4. 1
4.3
4.0
3.25
4.2
5.0
4.2
3. 4
3. 7
3.6
4. 15
3. 1
2. 1
4.7
78
118
95
94
136
105
<0. 1
<0.1
<0.1
<0.1
<0.1
<0.1
2.3
7.2
1.5
5. 1
16.5
7.2
Table 3-V. — Plasma Enzymes Determinations
Normal range,
units
aminases:
.GOT
SGPT
Esterase acetylcholine
Peptidase leucylamino
Aldolase
Isomerase phosphohexose .
Dehygrogenases:
Lactic
Malic
Succinic
Inosine
Alpha-ketoglutaric ....
Tsocitric
L-Glutamic
Alk phos
I
0 to 35
0 to 20
i 130 to 260
100 to 310
50 to 150
2 10 to 20
150 to 250
150 to 250
Neg.
Neg.
Neg.
Oto 10
0 to 10
Centrifuge
MR-4 flight
Prerun
15
8
260
190
19
Postrun
+ 30 min
19
8
215
250
28
170
140
Neg.
Neg.
Neg.
ApH units.
Bodansky units.
155
220
Neg.
Neg.
Neg.
-2 hr
13
8
280
200
22
Preflight
190
170
Neg.
Neg.
Neg.
-4 days
Postflight
+ 3 hr
+ 49 hr
19
21
28
6
6
7
225
205
165
370
375
385
6
13
3
42
86
17
190
250
220
235
275
220
Neg.
Neg.
Neg.
3
6
3
11
3
11
3
13
Table 3-VT. — Comparison of Physical Examination Findings During Simulated and Actual Flight
Simulated Redstone I
Simulated Redstone II
1
MR-4 High
temperature, r :
lie lore
y i .o
After
99.0
98.0
98.4
Change
] J
0.6
0.6
w eight, lb:
i j f\.
1 Z.H 11
llo.Zo
150.5
After
147.10
146.36
147.5
i ' „ . ,
oU I
o.U
1 ulse rate per mm:
Before
68
69
68
4iter
Oi
0,1
81 .
loo to HJ4
"I > 1 1 /T t \ TT
±>loo(i pressure (LA;, nim rig;
TJefore
110 '68
100 '70
128,73
\ft--r
100-70
128/80
120/84
Vital capacitv, liters;
'
■
Before
5.9
5.0
After
5.4
45
Postflight physical findings. . .
Chest clear to P and
Chest clear; DTR's
Chest clear; no pete-
A; slightly increased
2 + ; no petechia.
chia; appeared
DTR's; no change
fatigued.
in ECG; no pete-
chia; appears warm
and tired.
14
4. PHYSIOLOGICAL RESPONSES OF THE ASTRONAUT
IN THE MR-4 SPACE FLIGHT
By C. Patrick Lauchlin, M.D., Life Systems Division, NASA Manned Spacecraft Center; and William
S. Augerson, M.D., Life Systems Division, NASA Manned Spacecraft Center
Objectives
The space flight of Mercury-Redstone 4 accom-
plished several life-science objectives. Specifically,
a second United States astronaut experienced the
complex stresses associated with manned space
flight; physiological data reflecting the responses
of a second United States astronaut to space flight
were obtained ; and additional experience was gained
in the support of manned space flight which will
influence procedures in subsequent operations.
The Space Flight Environment
After two attempts at launching in the 4 days pre-
ceding the flight, Astronaut Grissom entered the
■raft at 3:58 a.m. e.s.t. on July 21, 1961. His
ation had proceeded smoothly, beginning at
1:10 a.m. e.s.t. as discussed in paper 5. He was
wearing the Mercury full-pressure suit and was posi-
tioned in his contour couch in the semisupine posi-
tion, with head and back raised approximately 10°
and legs and thighs flexed at approximately 90°
angles. This position was maintained until egress
from the spacecraft after landing. One-hundred-
percent oxygen was supplied when pressure suit con-
nections to the spacecraft environmental control sys-
tem were completed. The total time in the spacecraft
during the countdown was 3 hours 22 minutes. Dur-
ing the extended countdown, Astronaut Grissom per-
formed numerous spacecraft checks and "relaxed"
with periodic deep breathing, muscle tensing, and
movement of his limbs. At the lift-off signal, the
Redstone launch vehicle ignited and accelerated
smoothly, attaining a peak of 6.3g at T + 2 minutes
22 seconds. Then the spacecraft separated from the
launch vehicle and gravity forces were abruptly
terminated. A period of 5 seconds ensued while
spacecraft turnaround and rate damping occurred.
During the 5 minutes of weightless flight which fol-
\, Astronaut Grissom was quite active in per-
forming vehicle control maneuvers and with monitor-
ing of spacecraft systems. He was, in his own words,
"fascinated" with the view from the spacecraft win-
dow. The firing of the retrorockets at T + 5 minutes
10 seconds resulted in a brief lg deceleration. At
T + 7 minutes 28 seconds the 0.05g relay signaled
the onset of reentry, and deceleration forces climbed
quickly to llg. Drogue and main parachute actua-
tion occurred at T + 9 minutes 41 seconds and T +
10 minutes 13 seconds, respectively, and a 4g spike
was seen with opening of the main parachute. Land-
ing occurred at T + 15 minutes 37 seconds. 7:35
a.m. e.s.t.
Suit and cabin pressure levels declined rapidly
from launch ambient levels, as programed, and sta-
bilized at approximately 5 psia with the suit pressure
slightly above cabin pressure. These pressures were
maintained until snorkle valve opening at T + 9
minutes 30 seconds during parachute descent.
Suit inlet temperature ranged from 55° F to 62° F
during countdown and flight and reached a level of
73° F after approximately 9 minutes on the water
after landing.
Monitoring and Data Sources
Medical monitoring techniques and biosensor
application were identical with those utilized in the
MR-3 mission (ref. 1). The total monitoring time
was approximately 3 hours and 35 minutes, com-
mencing with entrance into the spacecraft and end-
ing in loss of signal after landing. Physiological
data were monitored from the medical consoles in
Mercury Control Central and the Redstone block-
house, and signals were received during the later
flight stages at Bermuda and on downrange ships.
Again the astronaut's inflight voice transmissions
and postflight debriefing were particularly signifi-
cant as data sources. (Samples of inflight tele-
metry data recorded at various monitoring stations
are shown in figs. 4-1 to 4-4.) In addition, the
15
1 Sec )> tj
Figure 4-L Blockhouse telemetry record obtained during countdown (5;43 a.m. e.s.t.).
canceled mission of July 19 with 4 hours of count-
down provided interesting comparative physiologi-
cal data. Astronaut Grisfiom's physiologic responses
to 17 Mercury- Redstone g-profile centrifuge runs
were also available as dynamic control data. Un-
fortunately, the astronaut: observer camera film was
lost with the sunken spacecraft.
Results of Observations of Physiological
Function
Figures 4-5 and 4-6 depict the pulse rate during
the countdown, tabulatec by a 10-second duration
pulse count for each minute of count time. Pulse
rates occurring at similar events in the canceled mis-
sion countdown are also indicated. The countdown
pulse rate ranged from 65 to 116 per minute until
shortly before lift'off. As plotted in figure 4-7,
pulse rate began accelerating from T— 1 minutes
through launch, attaining a rate of 162 beats per
minute at spacecraft separation and turnaround
maneuver. Some slight rate decline trend was ap-
parent during the first 2 minutes of weightlessness,
returning to a high of 171 beats per minute with
retrorocket firing. The pulse rate was above iaO
beats per minute during all but a few seconds of
weightlessness. Pulse rate declined slightly follow-
ing reentry deceleration and then fluctuated con-
siderably during parachute descent and was 137
beats per minute on landing. All inflight pulse rates
were determined every 15 seconds, counting for 10-
second durations.
Electrocardiographic trace quality from both
sternal and axillary leads was quite satisfactory dur-
ing countdown and flight. Sinus tachycardia and
occasional sinus arrhythmia were present. No ab-
normalities of rhythm or wave form were observed.
Respiratory rate during countdown varied from
12 to 24 breaths per minute as shown in figures 4—5
and 4-6. Unfortunately, respiratory trace quality,
which had been quite acceptable during countdown,
deteriorated during most of the flight, precluding
rate tabulation. Some readable trace returned late
in the flight, and a high of 32 breaths per minute
was noted.
Body temperature (rectal) varied from 99.5°
mediately after astronaut entry into the spac
16
to 98.6° just before launch. There was a gradual
v" se to 99.2° in the latter phases of flight. These
* i are considered to be insignificant, and, sub-
jectively, temperature comfort was reported to be
quite satisfactory during the countdown and flight.
Astronaut Grissom made coherent and appro-
priate voice transmissions throughout the flight. At
the postflight debriefing, he reported a number of
subjective impressions gained while in flight. He
noted that the vibration experienced at maximum
dynamic pressure was "very minor" and did not
interfere with vision. A brief tumbling sensation
was noted at launch-vehicle cutoff. This sensation
was only momentary and was not accompanied by
nausea or disturbed vision. A distinct feeling of
sitting upright and moving backward was described
and the sensation reversed to forward travel with
retrorocket firing. This orientation may have been
related to his position relative to Cape Canaveral;
that is, observing the Cape receding behind through
the spacecraft window. No disturbances in well-
being were reported during the flight and the ab-
sence of gravity produced no specifically recognized
symptoms. The astronaut was not aware of his
heart beating throughout the mission. Hearing was
adequate throughout the flight according to pilot
reports and voice responses. Near and distant
visual acuity and color vision appeared to be nor-
mally retained. The jettisoned escape tower was
followed for several seconds through the spacecraft
Change of record speed
Figure 4-2. Mercury Control Center record during launch phase {00:30 to 00:45). First part of record at 25 mm/sec,
second part at 10 mm/sec.
17
Figure 4—3. Bermuda Mercury Station record (10 mm/sec) taken just before 0,05g as period of weightlessness was
nearing end.
window and a planet (Venus) was observed just be-
fore burnout. Vivid contrasting color was reported
during observation of the sky and earth. The pro-
gramed turnaround and other maneuvers of the
spacecraft produced charging levels of illumination
within the cabin, necessitating considerable visual
adaptation.
Improved environmental control system instru-
mentation permitted a extermination of astronaut
oxygen consumption during the countdown. This
was calculated to be abou : 500 cc/min. A very high
usage rate was noted during flight as a result of
system leakage, and mettbolic utilization could not
be determined.
Astronaut Grissom's Mercury-Redstone centrifuge
pulse rates were tabulated and are presented graph-
ically in figure 4-7 for comparison with the flight
pulse data. The highest rate noted for his centrifuge
experience wras 135 beats per minute. Also shown in
figure 4-7 are Astronaut Grissom's respiratory rate
responses during four Mercury-Redstone centrifuge
sessions.
Conclusions
An evaluation of the physiological responses of
the astronaut of the MR^I space flight permits the
following conclusions:
18
W A/
r
W \
Respiratory trace. (Some variations represent speech)
i ■/,/|
ECG trace 1 (Axillary - small ampitude displacements due to muscle movement)
• \ v • V -V .v ! v V • V • V A v A ,v A ,.v A, v \ > ■■ A v . v- 'A * x '■
ECG 2 (Sternal) Showing sinus tachycardia
Body temperature trace
(99. 2°F)
Figure 4^1. Telemetry-aircraft record obtained 9 minutes after reentry.
(1) There is no evidence that the space flight
stresses encountered in the MR^l mission produced
detrimental physiological effects.
{2) The pulse-rate responses reflected Astronaut
Grissom's individual reaction to the multiple stresses
imposed and were consistent with intact perform-
ance function.
(3) No specific physiologic findings could be
attributed to weightlessness or to acceleration-
weightlessness transition stresses.
Reference
1. Henry, James P., and Wheelwright, Chari.es D. : Bioinstrumentatioti in MR-3 Flight. Proc. Conf. on Results of the
virst U.S. Manned Suborbital Space Flight, NASA, Nat. Inst. Health, and Nat. Acad. Sci., June 6, 1961, pp. 37^3.
19
Fig i re 4-6. Pulse and respiration rates during countdown (5:40 to 7:20 a.m. e.s.t.i.
20
5. FLIGHT SURGEON'S REPORT FOR MERCURY-REDSTONE
MISSIONS 3 AND 4
By William K. Douglas, M.D., Astronaut Flight Surgeon, NASA Manned Spacecraft Center
Introduction
This paper describes some of the operational as-
pects of the medical support of the two manned sub-
orbital space flights, designated Mercury-Redstone 3
and Mercury-Redstone 4. The results of the medical
investigative procedures are reported in paper 3 of
the present volume and in reference 1. These op-
erational aspects can be conveniently divided into
three phases:
(a) The early preparation period beginning
about 3 days before a launch and conclud-
ing at about T — 12 hours
(b) The immediate preflight preparation
(c) The debriefing period
Preparation of the Pilot
fart of the philosophy behind the decision to ex-
ecute manned suborbital space flights was to provide
experience and practice for subsequent orbital"
flights. In light of this philosophy, it was decided
that during suborbital flights all preparations will
be made for the orbital flight. This explains the
reason for such things as the low residue diet and
other seemingly inappropriate steps in the prepara-
tion and support of the pilot.
Three days before the planned launch day, the
pilot and the backup pilot start taking all of their
meals in a special feeding facility. Here, a special
low residue diet is provided. Preparation of this
diet is supervised by an accredited dietitian, and the
actual preparation is performed by a cook whose sole
duty during this period is to prepare these meals.
One extra serving of each item is prepared for each
meal. This sample meal is kept under refrigeration
for 24 hours so that it will be available for study
in the event that the pilot develops a gastrointestinal
illness during this period or subsequently. An effort
is also made to assure that several people eat each
meal so that an epidemiological study can be facili-
tated if necessary. The menu for these meals was
provided by Miss Beatrice Finklestein of the Aero-
space Medical Laboratory, Aeronautical Systems
Division, U.S. Air Force Systems Command. The
diet is tasty and palatable as is shown in table 5-1
which gives a typical day's menu. It has caused no
gastrointestinal upsets and is well tolerated by all
persons who have consumed it. In order to assure
that it would be well tolerated, all of the Mercury
astronauts consumed this diet for a 3-day period
during one of their visits to Wright-Patterson Air
Force Base in one of the early phases of their train-
ing program. The use of a separate feeding facility
provides the ability to control strictly the sanitation
of food preparation during this preflight period.
Such control could not as easily be exercised if
meals were taken in a community cafeteria.
During this 3-day period before the launch day,
the pilot lives in the Crew Quarters of Hangar "S"
which is located in the industrial complex of Cape
Canaveral. Here he is provided with a comfortable
bed, pleasant surroundings, television, radio, reading
materials and, above all, privacy. In addition to
protection from the curious-minded public, the estab-
lishment of the pilot and the backup pilot in the
Crew Quarters also provides a modicum of isolation
from carriers of infectious disease organisms. This
isolation is by no means complete and it is not in-
tended to be. An effort is made to provide isolation
from new arrivals in the community, however. It
is felt that a certain amount of natural immunity
has been acquired by the pilots in their day-to-day
contacts with their associates at the launch site.
Contact with visitors from different sections of the
country might, however, introduce a strain to which
no immunity had been acquired. Consideration was
given at one time to the use of strict isolation tech-
niques during this preparation period, but this
23
thought was abandoned because of its impracticality.
The pilot plays a vital role in the preparations for
his own flight. In order to be effective, a period of
strict isolation would have to last for about 2 weeks;
thus, the services of these important individuals
would he unavailable for that period. Further, it
was felt that a 2-week period of strict isolation would
constitute a psychological burden which could not
be justified by the results obtained. As mentioned
previously, the pilot and his colleagues play a vital
role in the preparation of the spacecraft and its
launch vehicle for the flight. This period begins
about 2 weeks prior to launch and continues up until
the day before the launch. During this period of
time, the pilot, on occasions, must don his full pres-
sure suit and occupy the role of "capsule observer"
during the course of certain checkout procedures.
Advantage is taken of these exercises to perform
launch rehearsals of varying degrees of sophisti-
cation. The most complete of these exercises occurs
during the simulated flight which takes place 2 or 3
days prior to the launch. This dress rehearsal dupli-
cates the launch countdown in event time and in
elapsed time, but it occurs at a more convenient hour
of the day. It not only enables those responsible for
the readiness of the spacecraft and the launch vehicle
to assure themselves of the status of these com-
ponents, but it also allows those directly concerned
with the preparation and insertion of the pilot to
assure themselves of the.r own state of readiness.
Finally, these exercises provide a certain degree of
assurance and familiarity for the pilot himself.
On the evening before the flight, the pilot is en-
couraged to retire at an early hour, but he is not re-
quired to do so. The pilot of MR-3 spacecraft re-
tired at 10:15 p.m. e.s.t, and the pilot of MR^l
spacecraft retired at 9:0C p.m. e.s.t. In both cases
the pilots fell asleep shortly after retiring without
benefit of sedatives or drugs of any kind. Their
sleep was sound, and insofar as they could remember,
was dreamless. The medical countdown for MR-4
flight called for awakening the pilot at 1 : 10 a.m. e.s.t.
(table 5-II). This time was 65 minutes later than
the wake-up time called for in the MR-3 countdown.
Time was saved here by allowing the pilot to shave
and bathe before retiring instead of after awakening
in the morning. Another 15 minutes was saved by
performing the final operational briefing in the
transfer van on the way to the launch pad, rather
than after arrival as was done in MR-3 flight. When
they were awakened on the morning of the launch,
both pilots appeared to have been sleeping soundly.
There was no startle reaction on awakening, and the
immediate postwaking state was characterir
eager anticipation and curiosity as to the pro'
the countdown. After awakening, the pilots per-
formed their morning ablutions and consumed a high
protein breakfast consisting of fruit, steak, eggs,
juice, and milk. No coffee was permitted during the
24-hour period preceding the flight because of its
tendency to inhibit sleep. No coffee was permitted
for breakfast on launch morning because of its
diuretic properties.
After breakfast, the pilots donned bathrobes and
were taken into the physical examination room where
the preflight physical was performed. This exami-
nation is distinct from that conducted for the purpose
of collecting background scientific data, which was
performed by several examiners 2 to 3 days prior to
the flight. This early examination is reported in
paper 3 of the present volume and in reference 1.
The physical examination performed on the morning
of the flight was designed to ascertain the pilot's fit-
ness to perform his mission. It was designed to dis-
cover any acute illness or infirmity which might
contraindicate the flight.
These examinations failed to reveal anything of
significance. The physiological bradycardia (pulse
rate 60 to 70 1 and normotensive (blood pressure
110/70) state both give some indication of the
reserved air of confidence which typifies h<
these pilots. It is important to emphasize at .„is
point that no medication of any kind was consumed
by either of these pilots during the several days pre-
ceding the launch. Following the preflight physical
examination, each of the pilots was given a short
battery of psychological tests. In the case of the
MR^l pilot, it was possible to provide a short inter-
view by a psychiatrist. Both the testing and the
interview were part of the medical investigative pro-
gram and are reported in paper 3 of the present
volume and reference 1. Suffice it to say at this point
that no abnormalities were detected.
The next step in the preparatory procedures was
the application of the biological sensor harness (figs.
5—1 and 5—2 ) . This harness is described in detail
in reference 2. The only difference between the
sensors used in MR-3 and MR^l flights was an
alteration of the respiration sensor housing for the
MR-4 flight to accommodate the microphone of
different configuration used in the later flight. The
surface of the electrode next to the skin is prepared
with an adhesive material identical to that found
on conventional adhesive tape (elastoplast '
24
Ficlre 5-1. Three views of a typical electrocardiograph floating electrode as used in Project Mercury. The surface of
the electrode applied to the skin (right) is first painted with adhesive and then filled with bentonite paste.
This preparation must be done at least 15
,tes in advance since the solvent for the adhesive
is irritating to the skin and must be given ample
opportunity to evaporate before the sensor is ap-
plied. The dermal surface of this electrode is first
filled with bentonite paste and the electrode is ap-
plied directly to the skin. The skin is first prepared
by clipping the hair where necessary and by cleans-
ing with surgical detergent (FSN 6505-116-1740).
The sensor locations have been previously marked
on all Mercury pilots by the use of a tiny (about 2
millimeters in diameter ) tattooed dot at each of the
four electrode sites. After the sensor is applied to
the skin, the uppermost surface of the screen is
covered with the bentonite paste and a small square
of electrician's plastic tape is applied over the opening
in the disk. The entire electrode is then covered
with a square of moleskin adhesive tape. This as-
sembly becomes, then, a floating electrode. The
electrician's tape serves to retard somewhat the evap-
oration of water from the bentonite paste.
The deep body temperature probe (fig. 5-2) is
simply a flexible rubber-covered thermistor. Since
it is difficult, if not impossible, to sterilize this probe
without causing deterioration of the device, each
pilot is provided with his own personal sensor har-
ness. This same harness is used in all practice exer-
cises in which the individual participates. It is
simply washed with surgical detergent after each
use.
After the harness is applied, the integrity of the
sensors is checked by the use of a modified Dallon
Cardioscope [fig. 5-3). With this device, both
electrocardiographic leads can be displayed on the
oscilloscope, and the amplitude of the QRS (Q-
wave, R— wave, S— wave) complex can be measured
roughly by comparing it with a standard 1 -millivolt
current. The integrity of the respiration sensor can
also be demonstrated by displaying the trace on the
oscilloscope. No effort is made to calibrate the
respiration sensor at this time. The temperature
probe is also checked by use of a Wheatstone bridge.
After the sensors have been applied, the pilot
moves to the pressure-suit room where he dons his
suit. Since the most uncomfortable period of the
countdown is that time spent in the suit, a check is
made with the blockhouse to determine the status
of the count. If there has been a delay or if one is
25
anticipated, the suit donning is held up at this point.
At some convenient time during the day before the
flight, the suit has been assembled and inflated to
5 psi, and a leak check is made. The "static" leak
rate is determined at this time. These values were
190 cc/min and 140 cc/min for the MR-3 and
MR— 1 flights, respectively. After the pilot has
donned his suit, he is placed in a couch in the pres-
sure-suit room and the suit is again inflated to 5 psi.
The ventilation flow is then turned off and a "dy-
namic'' leak rate is obtained by reference to the flow
of oxygen necessary to maintain this pressure. The
dynamic leak rate for the MR-3 flight was 400
cc 'min; for the MR— 4, it was 175 cc/min. The
term "leak rate" in this dynamic situation is used
rather loosely since it encompasses not only the ac-
tual leak rate of the suit but also the metabolic use
of oxygen. Exact measurement of this rate is
further complicated by the presence of a breathing
occupant of the suit; cianges in the occupant's
volume occasioned by respiratory movements are
reflected as changes in the flow rate, but a rough es-
timation is possible even under these circumstances.
After the pilot is laced in the couch but b ■' -*t
the dynamic leak rate is determined, the tor
per of the suit is opened and the amplifier fo. „e
respiration sensor is delivered. With the visor
closed, and with the microphone positioned as for
flight, the amplifier is adjusted to provide a signal
strong enough to be easily observed but not so
strong as to overload the spacecraft telemetry equip-
ment. Once the dynamic leak rate has been de-
termined, the suit is not again disturbed except to
open the helmet visor. No zippers are permitted to
be loosened from that time on. Upon completion
of the suit donning procedure, the pilot returns to
the examination room where the biosensors are
again checked on the oscilloscope. This would de-
tect any disturbance created by the donning of the
suit, and permit it to be corrected at this point rather
than later.
If the medical count and the main countdown are
still in agreement, a portable ventilating unit is at-
tached to the suit and the pilot and insertion team
proceed to the transfer van. Upon his arrival at
»" -nsfer van, the onboard ventilation system is
,-d. The integrity of the biosensors is again
checked by use of a Model 350, 8-channel Sanborn
recorder. The Sanborn recorder remains attached
to the pilot from this point on, and a continuous re-
cording of the measured biological functions is
started. A sample record taken while the van was
in motion is shown in figure 5-4.
Upon arrival at the launch site, two final strips
of record are obtained from the Sanborn recorder
and delivered to the medical monitors at the block-
house and at the Mercury Control Center. Both of
these records contain a 1 -millivolt standardization
pulse, and are utilized by the monitors to compare
with their records as obtained from the spacecraft.
When notified to do so by the blockhouse, the port-
able ventilating unit is reattached. The pilot, flight
surgeon, pressure-suit technician, and a pilot ob-
server (astronaut) leave the transfer van and proceed
up the elevator to the level of the spacecraft.
At this point, the preparation of the pilot ceases
and the actual insertion of the pilot into the space-
craft commences. After the pilot climbs into the
spacecraft and positions himself in the couch, the
pressure-suit technician attaches the ventilation
hoses, the communication line, the biosensor leads,
and the helmet visor seal hose, and finally, he attaches
the restraint harness in position but only fastens it
loosely. At this point, the suit and environmental
control system is purged with 100-percent oxygen
until such a time as analysis of the gas in the system
shows that the oxygen concentration exceeds 95 per-
cent. When the purge of the suit system is com-
pleted, the pressure-suit technician tightens the re-
straint harness; the flight surgeon makes a final in-
spection of the interior of the spacecraft and of the
pilot, and the hatch installation commences. During
-
Ficure 5-3. Cardioscope used to check out the biosensor harness. The lead into the suit is shown on the lower right, and
the switching box to display respiration and temperature is shown on the lower left.
27
Figure 5-4. Sample record f:om Sanborn recorder taken in the transfer van. The van was in motion at the
recording was made.
28
the insertion procedures, it is the flight surgeon's
to monitor the suit purge procedure and to
. by to assist the pressure-suit technician or the
pilot in any way he can. The final inspection of the
pilot by the flight surgeon gives some indication of
the pilot's emotional state at the last possible oppor-
tunity. The flight surgeon during this period is in
continuous communication w-ith the blockhouse sur-
geon and is capable of taking certain steps to analyze
the cause of biosensor malfunction, should it occur.
No such malfunctions occurred during the course of
these two flights. After hatch installation is com-
pleted, the flight surgeon is released and proceeds to
the forward medical station where he joins the point
team of the land recovery forces.
Debriefing
After a successful launch, the flight surgeon leaves
his position on the point team and proceeds imme-
diately to the Mercury Control Center. Here he fol-
lows the progress of the recovery operations until
it is clear where his services will be needed next. In
the event the pilot is injured or is ill. the flight sur-
geon is taken by air to the aircraft carrier in the
recovery area. If it is clear that the pilot is unin-
jured, as was true for MR-3 and MR^t flights, the
flight surgeon joins the debriefing team and is flown
\e medical care and debriefing site at Grand
.ma Island, British West Indies. During this
time, the pilot is undergoing a preliminary physical
examination and debriefing aboard the carrier. In
both of the flights under discussion, the debriefing
team arrived at Grand Bahama Island about 30 min-
utes before the pilot who was flown there from the
carrier. The debriefing site is a two-room prefabri-
cated building with an adjacent heliport. The heli-
port is provided in the event it is more convenient,
or is necessary by virtue of his physical status, to
carry the pilot from the surface vessel to the de-
briefing site by helicopter.
Immediately upon their arrival at Grand Bahama
Island, the pilots were taken to the debriefing build-
ing where the flight surgeon performed a careful
physical examination. Here again, the purpose of
this examination was not so much to collect scientific
material as to assure that the pilot was uninjured
and in good health. When this preliminary exam-
ination had been completed, the pilots were exam-
ined by a surgeon. No evidence of injury was
found by this second examiner. Next, an internist
examined the pilots. Laboratory specimens (blood
urine) were obtained and the pilots were exam-
ined by an ophthalmologist, a neurologist, and a
psychiatrist. Chest X-rays (anteroposterior and
right lateral) were taken. The results of all of
these examinations were, in the main, negative and
have been reported in paper 3 of the present volume
and reference 1 . Upon completion of the physical
examination, the pilots were turned over to the engi-
neering debriefing team.
The original plan for the pilot's postrecovery
activities permitted him to remain at Grand Bahama
Island for 48 hours after his arrival. This period
was believed to be necessary to permit full and ade-
quate recovery from the effects of the flight. In the
case of the MR-3 flight, it was possible for the pilot
to remain for 72 hours. The last day of this period
was devoted to complete rest and relaxation. The
additional 24-hour period was occasioned by the
scheduling of the postflight press conference and
public welcome in Washington, D.C. It was quite
apparent that the postflight rest period was benefi-
cial to the pilot. There is no objective measurement
of this, but the day-to-day observations of the pilot
showed him to be benefited by this relative isolation.
In the case of the MR— 4 flight, the pilot seemed to
be recovering rapidly from the fatiguing effects of
his flight and the postflight water-survival experi-
ence. His fatigue was more evident when seen 12
hours after his arrival at Grand Bahama Island than
that observed in the pilot of the MR-3 flight when
seen at the same time. On the following day, how-
ever, the MR— 4 pilot seemed to be at about the same
level of recovery as had been observed in the MR-3
pilot. For this reason, it was decided to permit the
pilot of the MR-4 flight to return to Cocoa Beach,
Fla., for a press conference at a time some 18 to 20
hours before that called for in the original plan.
No evident permanent effects of this early return
can be described, and the pilot performed well in
his public appearances: but his fatigue state was
much longer in dissipating as he was seen in the
davs subsequent to the flight. Again, this slower
recovery cannot be demonstrated with objective
findings, and must be accepted only as a clinical
observation of the writer.
Concluding Remarks
The flight surgeon's activities and duties in sup-
port of two manned suborbital flights have been de-
scribed and certain observations of the flight surgeon
have been recorded. In summary, it is important
to point out three items.
29
(1) During the 12-hour period preceding the
launch, it is vital that the preparation of the pilot
follow the countdown with clocklike precision. This
precision becomes more urgent as the time ap-
proaches for insertion of the pilot into the space-
craft. In order to accomplish this precision, it is
necessary to practice the preparation procedures
time and time again. Time-motion studies are nec-
essary. In the training program for the Mercury
flights, each insertion of as astronaut into the cen-
trifuge was performed just as if it were a real launch.
At times during the checkout of the spacecraft, it
was necessary to insert an astronaut into the space-
craft in an altitude chamber. Each of these events
was conducted as for a launch. Even with these
manv opportunities to practice and perfect tech-
niques, some changes were made after the MR-3
flight for the MR^i flight. The fact that no delays
were occasioned by the preparation procedures at-
tests to the value of these repeated practice sesf
(2) Very early in the planning for manned .
flights, it was decided to train a backup man tor
each position in the medical support complex. A
backup astronaut was always available; a backup
flight surgeon was trained; and even a backup
driver for the transfer van was available. These
backup men not only provided substitutes of ready
accessibility, but also permitted each person involved
to get some rest on occasion. The primary individ-
ual was then capable of performing his task in an
alert and conscientious manner on the actual day
of the launch.
(3) In future manned flights, the planned 48-
hour minimum debriefing period should be ob-
served and even extended to include a 24-hour
period of complete rest if indicated by the stresses
experienced during the flight.
References
1. Jackson, C. B., Douglas, William K., et aL: Results of Preflight and Postfiight Medical Examinations. Proc. Conf.
on Results of the First L.S. Manned Suborbital Space Flight, NASA, Nat. Inst. Health, and Nat. Acad. Sci., June fi,
1961, pp. 31-36.
2. Henry, James P., and Wheelwright, Charles D.: Biomedical Instrumentation in MR-3 Flight. Proc. Conf. on Results
of the First U.S. Manned Suborbital Space Flight, NASA, Nat. Inst. Health, and Nat. Acad. Sci., June 6, 1961,
pp. 37-43.
Table 5-1. — Sample Low-Residue Menu
[Third day prior to space flight]
Breakfast :
Orange juice 4 ounces
Cream of wheat Vj cup, cooked
Cinnamon or nutmeg Few grains
Scrambled eggs 2
Crisp Canadian bacon 2 to 3 slices
Toast I white bread) 1 to 2 slices
Butter 1 teaspoon
Strawberry jelly 1 tablespoon
Coffee with sugar No limit
Lunch :
Chicken and rice soup -1 cup
Hamburger patty 3 to 4 ounces
Baked potato (.without skint 1 medium
Cottage cheese 2 rounded tablespoons
Bread (white) 1 to 2 slices
Butter 1 teaspoon
Sliced peaches (canned)
V-i cup
Coffee or tea with sugar No limit
Dinner:
Tomato juice 4 ounces
Baked chicken (white meat) 4 ounces
Steamed rice 1 cup
Pureed peas '/i cup
Melba toast 1 to 2 slices
Butter 1 teaspoon
Lemon sherbet % cup
Sugar cookies 2 to 3
Coffee or tea with sugar No limit
30
Table 5— II. — A Comparison of the Medical Countdown of MR-3 and MR-4 Flights
MR-3 flight
MR-4 flight
Event
T — thne^
a.m.
T — time,
a.m.
mm
est
T'T
e'« '
0)
(-')
— 355
1:07
-290
1:10
1 { I-f- Q t ("flit
-310
1:45
-275
1:30
-280
2:27
-245
1:55
-250
2:48
-215
2:15
^iiit nAniiino
-240
3:07
-205
2:55
— 2 J.U
1/3
J.lO
Enter transportation van
-185
4:09
-150
3:28
Arrival at launch pad
-155
4:31
-125
3:54
-155
4:31
Omitted
Omitted
-130
5:15
-125
3:55
-118
5:21
-122
4:00
0
9:34.13
0
7:20:36
1 Planned time during countdown according to the launch document.
2 Actual time event occurred.
31
6. RESULTS OF INFLIGHT PILOT PERFORMANCE STUDIES
FOR THE MR-4 FLIGHT
By Robert B. Voas, Ph. D-, Head, Training Office, NASA Manned Spacecraft Center; John J. Van Bockel,
Training Office, NASA Manned Spacecraft Center; Raymond G. Zedekar, Training Office, NASA
Manned Spacecraft Center; and Paul W. Backer, McDonnell Aircraft Corp.
Introduction
This paper presents a second report on the ability
of the pilot to operate the space vehicle and perform
all associated space-flight functions during Mercury
flights. As with the previous paper, the analysis is
directed toward establishing the capability of the
man to perform in the weightless environment of
space with essentially the same proficiency which he
demonstrates under the more normal terrestrial con-
ditions. The results of the analysis of the MR-3
flight indicated that the pilot was able to perform
the space-flight functions, not only within the toler-
ances required for the successful completion of the
mission, but within the performance levels demon-
led in fixed-base trainers on the ground under
tially optimal environmental conditions. From
i.,c first manned Mercury-Redstone flight, it was con-
cluded that the performance data were essentially in
keeping with the previous experience with manned
aircraft flying zero-g trajectories. That is, the
pilot was able to operate the space vehicle and per-
form other flight functions while exposed to the un-
usual environmental conditions of space, including
a 5-minute period of weightlessness, without a de-
tectable reduction in performance efficiency. As in
the MR-3 flight, the astronaut's communications to
the ground provide one source of data, while the
telemetered records of vehicle attitude under manual
control provide a second source, and a third source is
the narrative description of the activities and events
given bv the pilot during the postflight debriefing.
Xot available for this report are the onboard pic-
tures of the astronaut, since the film was lost with
the spacecraft. This paper attempts to evaluate the
performance of the pilot on the MR-4 mission, to
compare the observations made by Astronaut Shep-
ard and Astronaut Grissom of the earth and sky,
as seen from space, and to compare their evaluations
he Mercury training devices.
The Astronaut's Flight Activities Plan
Three major differences between the MR^l and
MR-3 flights which are of significance to the astro-
naut's activities can be noted. First, spacecraft no.
11 (MR^l) differed from spacecraft no. 7 (MR-3)
in that spacecraft no. 11 had available the center-
line window which permits a view directly in front
of the spacecraft. Through this window, the astro-
naut is able to see 33° in a vertical direction and
approximately 30° horizontally. With the space-
craft in the orbit attitude, which is —34° with the
small end down, two-thirds of the window is filled
with the earth's surface and the upper one-third
views space above the horizon. The size and loca-
tion of this window provided an opportunity for
better examination of the earth's surface and ho-
rizon than was possible through the 10-inch-diam-
eter porthole available to Astronaut Shepard. The
second variation from the MR-3 flight was in the
checkout of the various reaction-control systems
(RCS). During the MR-3 flight, Astronaut Shep-
ard made use of the manual proportional and the
fly-by-wire control systems, whereas during the
MR^ flight, Astronaut Grissom made use of the
manual proportional system and the rate command
system.
The third variation between the MR-3 and MR-4
flights was a slight reduction in the number of flight
activities following the retrofire period on the MR^f
flight. The flight programs for Astronaut Shepard
and Astronaut Grissom are compared in figure 6-1.
Each begins with essentially the same launch period
during which the astronaut monitors the sequential
events and reports the status of the onboard systems
approximately every 30 seconds. In both flights,
the turnaround maneuver was performed on the au-
topilot with the astronaut monitoring the autopilot
action. Immediately after the turnaround, both As-
tronaut Shepard and Astronaut Grissom selected the
33
CONTROL SYSTEM IN OPERATION
MR-4
A.S
c s|
Hi P. |
R 5 C 5
MR-3
A.S. | 1 j 2 |
CS. AXIS AXES
M. P. |
F. B. W.
1 A.SCS. | M.P. l
1 1
m. <f - M. v.
PRIMARY REFERENCE SYSTEM
A. S. C. S- - AUTOMATIC STABILIZATION AND CONTROL SYSTEM
MP - MANUAL PROPORTIONAL
R. S, C S
F. B. W. -
FLY BY WIRE
MR-4
INSTRUMENTS _ WINDOW
1
INSTRUMENTS
MR-3
INSTRUMENTS
1 PERISCOPE 1
INSTRUMENTS
1
ATTITUDE SUMMARY MR-3
ALL NORMAL MANUAL ATTITUDE CHANGES ARE MADE AT 4° PER SEC
ROLL
2:55
IN
ORBIT
3:10
1:50
ON
s:ope
ATTITUDE SUMMARY MR-4
PITCH hO -M°
YAW
- 0
-34°
-14
0
-34°
0
— w
-20°
V_/
-20°
RFJROF I RE
4:41 4:56 5:11 :
RETRO- IN RETR0-
SEO. RETRO FIRE
5:33 5:40
END F. B. W.
RETRO
2:50 3:00
IN
RETRO
w
-20°
\
/
-45°
\__/
-2')°
4:00
WINDOW
REFERENCE
RETRO-
FIRE
4:30 4:45
TO RETRO
RETRC SEQUENCE
5:10
RETRO-
FIRE
5:33
END RETRO
TO A. S. C. S.
/
+40°
-20"
6:20 6:35 ML
TO IN SCOPE
REENTRY REENTRY RETRACT
6:10
RETROS
JETT.
6:40
SCOPE
RETRACT
7:40
.05g
A. S. C. S.
«40»
/
-34°
Fit lre 6-1. Manual control summary for the MR-3 and MR^i flights.
manual proportional control mode and attempted to
make a series of maneuvers : one each in pitch, yaw,
and roll using the spacecraft attitude and rate indi-
cator as a reference. After these three basic ma-
neuvers, the astronaut shifted to an external
reference. During this period. Shepard used the
periscope, whereas Grissorr. used the window. Each
reported what could be seen through these observa-
tion systems. In addition, Grissom made a 60° left
yaw manuever to the south.
Following this period on external reference, the
retrofire maneuver started. This maneuver com-
menced with the countdown from the ground to the
retrosequence. From the retrosequence to the start
of retrofire, there is a 30-second period during which
the astronaut brings the vehicle into the proper at-
titude for retrofiring. This is followed by a retro-
rocket firing period of approximately 20 seconds.
Both Astronaut Grissom and Astronaut Shepard
controlled the spacecraft attitude during this period
using the instrument reference and the manual pro-
portional control system.
Following retrofire, Astronaut Shepard attempted
to do a series of maneuvers using the fly-by-wire
system and the spacecraft instruments as a refer-
ence. This series of maneuvers was omitted for
Astronaut Grissom's flight; instead, he switched to
the rate command system and returned to the
window reference for further external observations.
During this period both Astronaut Shepard and
Astronaut Grissom made a check of the HF com-
munications radio system.
The next mission phase began at approximately
T + 6 minutes 40 seconds with the astronaut pitch-
ing up to reentry attitude. At this point, both
Astronaut Shepard and Astronaut Grissom looked
for stars, Shepard using the small porthole on his
left and Grissom using the large centerline window.
Neither astronaut was able to see any stars at this
time.
34
Following this period of observation, the reentry
l~" "n. Astronaut Shepard used the manual pro-
nal control mode and rate instruments to
t. *ol the reentry; whereas Grissom used the rate
command control mode and rate instruments during
this period. Since the reentry oscillations caused
no discomfort or concern, little control was exer-
cised by either astronaut.
Although Astronaut Grissom had been relieved
of some of the attitude maneuvers that were required
of Astronaut Shepard between the retrofire and the
reentry period, his program was still a full one.
These full programs resulted from the decision to
make maximum use of the short weightless flight
time available during the Redstone missions.
Attitude Control
The curves of figure 6-2 are the attitudes of pitch,
yaw, and roll maintained by Astronaut Grissom
throughout the flight. The shaded area in the back-
ground indicates the envelope of attitudes main-
tained during 10 Mercury procedures trainer runs
the week prior to the MR— 4 flight. As described
in paper 2 of this volume, there was a malfunction
of the manual proportional control system. This
malfunction resulted in Astronaut Grissom s receiv-
ing less than the normal amount of thrust per control
,r deflection. This anomaly in the performance
; manual proportional control system resulted
.ie first three maneuvers being performed some-
what differently from those on the trainer, though
generally still within the envelope of the trainer
runs. The pitch and yaw maneuvers overshot the
20° desired attitude, and the time to make each
maneuver was somewhat increased. This longer
maneuvering time in pitch and yaw, plus the time
required to remove residual roll rates, prevented
the attempt to make the roll maneuver. It is inter-
esting to note that Astronaut Shepard on his flight
was also pressed for time at this point and cut the
roll maneuver short, rolling only 12° instead of 20°.
Following these three attitude maneuvers, Astronaut
Grissom made a left yaw maneuver of approxi-
mately 60°, using the manual proportional control
mode and window reference. This maneuver was
performed approximately as it was during the
trainer sessions.
Both Grissom and Shepard maintained the at-
titude of the spacecraft manually during the firing
of the retrorockets. During the critical period of
approximately 20 seconds in which the retrorockets
were firing, the attitudes were held very close to the
proper retroattitude of 0° in roll and yaw and — 34°
in pitch. The accuracy with which Astronaut Gris-
som held these attitudes is shown by the curves in
figure 6-3 with the envelope of trainer runs in the
background. The permissible attitude limits inside
of which the retrorockets can be fired are shown as
the extents of the ordinate scale labels. Outside of
these limits, the retrorocket firing sequence would
be interrupted until all the attitudes returned to
within the permissible limits. Attitude control
performance during this period was well within
the limits required for a safe landing from orbit
in the planned recovery area. The pilot stated
during the debriefing that controlling attitude
during the retrofire for the MR-4 flight appeared
to be about equal in difficulty to the procedures
trainer. For the training runs, using the fixed-
base trainer, retrorocket-misalinement levels were
selected which simulated misalinement torques
equal to approximately 60 percent of the available
reaction control system control torque. Since
it is not possible to measure the retrorocket-
is yxi 5» im Tm T» Ild tSi wo 135 itc s-a. s-it s?5 ?55 53i Tto-
■'iW WJN'SEC
c.t l-B icX ts
:JC ':JC :.50
Figure 6-2. The MR-4 flight attitudes with four trainer runs in the background.
35
-46.5 r-
PERMI SSI BLE
PITCH, -340 -
DEG
-2L51-
-30, —
PERMISSIBLE
YAW 0
OEG
PERMISSIBLE
ROLL, 0
DEG
+30 1 —
RETRO
MO.
05:03.6
re™
NO. 2
05:13.3
RETRO
NO. 3
mm?
J L L
5:05
l l l
5:10
I I i
5:i5
'////////// ENVELOPE OF 4 PROCEDURES TROVER Rj\|S
5:20
5:25
5:30
5:35
Figi 'he 6-3. Attitude control during MR-4 retrofire period.
misalinement torques actually encountered during
the flight, the performance of the system and of the
pilot cannot be evaluated iti detail. In addition, the
pilot's assessment of the retrofire difficulty level may
be a result of reduced effectiveness of the manual
proportional control system, rather than large retro-
roeket-mislinement torque levels.
Following the retrofire period. Astronaut Gris-
som shifted to the rate conmand control and main-
tained the spacecraft attitude at —34° pitch and 0C
roll and yaw until T + 6 minutes 34 seconds, at which
time he pitched to the proper reentry attitude. The
attitude control during this, period is well within the
envelope demonstrated during the fixed-base trainer
runs. During the rentry, :he pilot made use of the
rate command system, waich provides automatic
rate damping to ±3 deg sec if the stick is main-
tained in the center position. This system appeared
to work well and no control action was required of
the pilot to damp rates.
In summary, the pilot was able to accomplish the
majority of the planned attitude maneuvers, despite
the malfunction of the conLrol system. This fact,
together with the excellent control performance dur-
ing the critical retrofire portion of the mission, pro-
vides an indication that pilot's control performance
was not degraded during the approximated 5
minutes of weightless flight.
Flight Voice Communications
Ninety-four voice communications were made by
Astronaut Grissom between lift-off and impact.
(See appendix.) As in Astronaut Shepard's flight,
these voice communications provide an indication
of how well the astronaut was able to keep up with
the mission events, how accurately he was able to
read his cockpit instruments, and how well he was
able to respond to novel and unusual events during
the flight. In general, the astronaut made all of the
normal reports during the launch and reentry at
the times appropriate to the event. His instrument
readings relayed to the ground showed general agree-
ment with telemetered data. In addition to the
standard voice reports of spacecraft events and i"-
36
strument readings. Astronaut Grissom made a num-
l c unscheduled reports of the unique events of
,'ht. He reported and described the unique
vik« through the centerline window and the prob-
lem with the attitude control system.
Pilot Observations
The major sensory observations made by the
pilots during the MR-3 and MR-4 flights were those
of vision, auditorv phenomena, vibration, angular
acceleration, linear acceleration, weightlessness, and
general orientation.
Vision
On the MR— I flight. Astronaut Grissom used the
centerline window for the bulk of his external ob-
servations, whereas Astronaut Shepard primarily
used the periscope. The major areas of observation
are listed as follows:
Earth's surface. — Astronaut Grissom was ham-
pered in his attempts to identify land areas due to
extensive cloud coverage. He was, however, able
to make some observations as evidenced by the fol-
lowing quotations from the postflight debriefing
sessions: "". . . The Cape is the best reference I
had. ... I could pick out the Banana River and
see the peninsula that runs on down south, and then
vn the coast of Florida. I saw what must have
West Palm Beach . . . and it was a dark
brown color and quite large. I never did see Cuba.
High cirrus blotted out everything except an area
from about Davtona Beach back inland to Orlando
and Lakeland to Lake Okeechobee and down to the
tip of Florida. Be\ond this the Gulf of Mexico
was visible."
Astronaut Shepard was less hampered by cloud
formations during his flight. His observations
through the periscope were reported as follows in
the postflight debriefing sessions: '". . . The west
coast of Florida arid the Gulf coast were clear. I
could see Lake Okeechobee. I could see the shoals
in the vicinitv of Bimini. I could see Andros Is-
land . . . Tampa Bay. . . . There was an abrupt
color change? between the reefs, in the area of Bimini
and the surrounding water/'
Clouds. — Because of shortage of time and/or
high cirrus clouds that obscured any underlying
vertical cloud formations, neither Astronaut Shep-
ard nor Astronaut Grissom was able to report cloud
I- ' his during the MR-3 and MR-4 flights.
Horizon. — Astronaut Grissom described the hori-
zon as "verv smooth as far as I could see ... a
blue band above the earth, then the dark skv. It
is very vivid when you go from the blue to the
dark. . . . The blue band appears about a quarter
of an inch wide."
Astronaut Shepard viewed the horizon through
the small 10-inch-diameter porthole. He described
bis view as follows: ". . . There was only one haze
layer between the cloud cover and the deep blue. . . .
ft was a little hazy, or what looked like haze; so there
was no real sharp definition between clouds, haze
layer, or the horizon and skv.
Sky. — Astronaut Grissom reported that the skv
was verv black and that the transition from blue to
black was very rapid during the launch phase.
Astronaut Shepard on the MR-3 llight had the
impression that the skv was a very dark blue rather
than black.
Stars. — The high contrast between the cabin in-
terior light intensity and external areas for both
suborbital flights made it verv difficult for either
pilot to locate stars. Astronaut Shephard did not
see any stars during his flight. Astronaut Grissom
was not able to locate any stars during the scheduled
external observation period of his flight; however, he
did locate what appeared to be a star late in the
powered phase of the llight. Subsequent investiga-
tions indicate that he saw the planet Venus.
Sun. — The sun never posed a great problem for
either of the astronauts during the suborbital mis-
sions. It entered the cabin either directly or reflected
during both (lights, I nlike Shepard. Astronaut
Grissom did have some minor difficulties with sun-
light. His statements were: "The sun was coming
in bright at 0.05g and I think I would have missed it
if I hadn't known that it was due and coming
up. ... I looked real close and I did see it. . . .
It conies in pretty much as a shaft of light with every-
thing else in the cockpit dark,
L se of earth reference for attitude control. — Both
astronauts expressed confidence that it would be
possible to determine rates and attitudes by the use
of their respective available external reference de-
vices. Astronaut Shepard said. "Qualitatively. I
noticed nothing that would prevent it [periscope]
from being a good backup for the instruments, for
attitude reference and for control.
Astronaut Grissomrs comments on the window as
a means of reference were : "When I had zero roll
on the instruments. I had zero roll out the window.
When I was looking at the Cape, then I had a good
37
reach' van reference and then it [yaw rate | was quite
apparent, and I could eont :ol on that basis.
Other visual phenomenc. — Neither pilot was able
to observe the launch vehicle at any time during the
flights. At tower separation, the periscope has not
as vet extended so Shepard was not able to observe
the tower jettisoning. However, the centerline win-
dow provided Grissoin with a direct view of this op-
eration. His comment is as follows: "I didn't see
anv (lame, but I could see t go and I could see it for
a long time after it went. I could see the little tail-
off and it occurred to me that it went slightly off
to my right.
Both pilots were able to observe through the peri-
scope some portions of tht retropackage after it had
been jettisoned. Astronaut Grissom's comment was :
"'Right after retrojettison. I saw something floating
around. It actually looked like a retromotoi' at one
time, and these floated by a couple of times.
Astronaut Shepard's conment was: "I heard the
noise and saw a little hit o:' the debris. 1 saw one of
the retropacks retaining straps.
During the reentrv phase. Astronaut Grissom re-
ported observing what he describes as shock waves.
His report was: "I'm fairly certain it was shock
waves off the shield of th 3 capsule. It looked like
smoke or contrail really, but I'm pretty certain it
was shocks.
Drogue parachute deployment was observed by
both pilots. Shepard observed this event through the
periscope and Grissom through the centerline
window. Astronaut Shspard reported: "The
drogue | parachute ] came out at the intended alti-
tude and was clearly visible through the periscope."
Astronaut Grissom observed: "The drogue
[ parachute ] came right out. I could see the canister
go right on out and the drogue deploy."
Main parachute deployment was obvious to both
pilots. Astronaut Grissom was afforded the best
\ iew of the parachute through the centerline window.
Astronaut Grissom reported: "1 could see the com-
plete chute when it was in the reefed condition and
after it opened I could ?ee. out the window. 75
percent of the chute.'7
Astronaut Shepard's comment was: "Then at
10.000 feet, of course, the antenna canister went off.
and you could see it come < ff and pull the main chute
with it and then go off in the distance. ^ ou could see
the chute in the reefed condition. Then it dereefed.
When asked. "Did you see the chute at full infla-
tion?'* he replied. "Yes. I vould say probably three-
fifths of the chute area : over half, anyway. "
Astronaut Grissom observed the reserve parachute
canister in the water through the periscope af' '*
had jettisoned.
Astronaut Grissom was not able to locate ai. .1
the recovery ships or search aircraft. Shepard was
able to see the search aircraft in the recovery area.
He reported during the debriefing. 'T didn't see anv
airplanes out the scope until after I had hit. but I
saw the choppers through the "scope after impact.*
Auditory Phenomena
The noise encountered by both pilots did not at
any time reach a disturbing level. The major
mechanical functions of the spacecraft were audible
to both astronauts. Their reports of the various
functions are as follows:
Shepard observed: "Sounds of the booster
[launch vehicle |. the pvros [pyrotechnics] tiring,
the escape tower jettisoning, and the retros bring
could be heard. All these sounds were new:
although none of them was realv loud enough to be
upsetting, thev were definitely noticeable. I remem-
ber thinking 1 did not hear the noise of the manual
jets firing. I was aware of the posigrade firing and
of just one general noise pulse.
Grissom reported: "At no time did we have anv
annoying sound level, ^ou can hear the escape
rocket fire, the posigrades. and \ ou can hear 'lie
retrorockets fire and feel them. *i ou can he;
pitch and v aw jets fire, and that's about it."
Both astronauts reported that thev heard the
retrorocket package jettison and heard the firinu of
the drogue-parachute mortar. However, only Shep-
ard recalled hearing the antenna mortar firing.
Vibration
The vibrations encountered b\ Astronaut Grissom
during the MR— 4 flight were less than those ex-
perienced by Astronaut Shepard on the MR-3 flight.
This was primarily a result of ill an improved
fairing between the spacecraft and the launch vehicle
and (2 1 added sound attenuating material in the
couch. Vibration was experienced only during the
launch phase of both flights. The astronauts reports
of the vibrations encountered and their effects are
as follows. Shepard's comments were: "'From the
period of about 45 to 50 seconds after lift-off and
through about a minute and a half there was some
vibration. I could feel vibrations building up. and
the sound level came up a little bit until at one
point. I'm not sure whether it was at max q | maxi-
mum dynamic pressure] or not. there wras eno" '"
38
vibration in the capsule j spacecraft] thai there wa? a
/ "~ f iizzv appearance of the instrument needles.
after we got through max q, everything
smoothed out." The degradation of vision asso-
ciated with this vibration was not serious.
Grissom observed: "I called out vibrations as soon
as thev started and they never did get very bad at
all. 1 was able to see the instrument panel and see
the instruments clearly all the time and to transmit
quite clearly.'
Angular Acceleration
Astronaut Grissom reported that he was able to
discern angular accelerations during spacecraft turn-
around and retrofire. He did not think that he could
feel the accelerations produced in controlling the
spacecraft:
Astronaut Shepard had much the same experience
on the MR-3 flight. He was also able to feel the
angular accelerations during periods when there
we iv high torques acting on the spacecraft.
Linear Accelerations
Both pilots were aware of the linear accelerations
connected with the main functions of the spacecraft,
such as posigrade firing at spacecraft separation,
retrorocket firing, reentry, drogue parachute deploy-
s'—I. main parachute deployment, and impact. In
>n. Astronaut Grissom was able to identify the
anient of the landing bag. He stated, 'T could
feel it [the landing-bag deployment!, but it was just
a slight jar as the thing dropped down."1
Astronaut Shepard stated that the landing-bag
shock was so slight that he did not notice it.
^ eiglitle^ne-s
Both pilots experienced approximately the same
-ensations during the weightless phase of the flight.
The\ both had to make a special effort to notice the
weightless condition. Astronaut Shepard made these
observations concerning his flight: T said to myself.
"Well. OK. vou've been weightless for a minute or
two and somebody is going to ask you what it feels
like/ ... In other words. I wasn't disturbed at all
by the fact that I was weightless. I noticed a little
bit of dust living around, and there was one washer
over iiiv left eye. . . . I w as not uncomfortable and
1 didn't feel like my performance was degraded in
anv «av, No problems at all.
Astronaut Grissom's primary cue to the weight-
less condition was also a visual one. as is indicated
by his comments during the debriefing: ". . . At
zero-g. everything is floating around, f could see
washers and trash floating around. I had no other
feeling of zero-g: in fact. I felt just about like I
did at Ig on mv back or sitting up. '
General Orientation
Neither pilot experienced any unexpected disori-
entation. Astronaut Shepard, in fact, experienced
no disorientation at any time as is indicated by his
statements during the debriefing.
Astronaut Grissom. on the other hand, experi-
enced a slight pitching forward sensation at launch-
vehicle cutoff. His comment was : ". . . Right at
BECO [booster-engine or launch-vehicle cutoff]
when the tower went. I got a little tumbling sensa-
tion. I can't recall which way it was that I felt I
tumbled, but I did get the same sort of feeling that
we had on the centrifuge. There was a definite
second of disorientation there. I knew what it was.
so it didn't bother me." Most of the astronauts have
experienced this sensation during this period on
dynamic centrifuge simulations. Grissom further
commented: 'Trior to retrofire. I really felt that
I was moving: I was going backwards. . . . When
the retros fired. I had the impression I was very
definitely going the other way .
Training Program Evaluation
The Mercury astronaut training program was de-
scribed by Astronaut Slayton in the report on the
Mercury-Redstone flight 3 i ref. 1). As a result of
the two suborbital flights, a preliminary evaluation
of some portions of the training program are pos-
sible. The pilots' comments on some of the more
important phases of training are given in this section.
General Comments
Astronaut Shepard reported that he felt suffi-
ciently trained for the mission. He felt that the
training produced a ". . . feeling of self-confidence
as well as the phy sical skills necessary to control the
yehicle." He did not believe that any area? of train-
ing had been neglected. He reported. ". . . that
as a result of the training program, at no time during
the flight did 1 run into anything unexpected."'
With regard to items in the training program which
might be omitted. Astronaut Shepard reported. "All
the training devices and phases we experienced were
valuable.'' However, since he felt that the physio-
39
logical svmptoms associated with weightlessness and
other space flight enviror mental conditions were not
going to be a problem, he believed the time devoted
to weightless flights and disorientation devices could
he reduced.
Astronaut Grissom stated after the flight that he
felt least well prepared in the recovery portion of
the mission. He also felt that additional practice
on the air-lubricated free-attitude trainer during the
last 2 weeks prior to the mission would have been
desirable. This simulate r is at NASA-Langley Air
Force Base. Va.. and not available to the astronaut
who must remain close to the launch site just prior
to the flight. Astronaut Grissom also felt he should
have had more time at the planetarium and for map
stud\. Like Astronaut Shepard, he did not feel any
of the training phases v ere unnecessary, but that
the time on some trainers could be reduced.
Weightier Flying
Astronaut Shepard reported that. '\ . . The weight-
less flving is valuable as a confidence-building ma-
neuver." Astronaut Grissom agreed that the train-
ing was valuable and that he would not want to be
without it. Both reported that the flights in the F-
100 airplanes in which ihey experienced 1 minute
of weightlessness, while strapped in the seat, were
most similar to their Kedstone-Mercury flight ex-
periences. Shepard felt that the amount ol weight-
less flying could have been reduced.
Fixed-Base Procedures Training
Both pilots felt this was a very valuable trainer,
particularly when tied into the Mercury Control
Center simulations. Ast onaut Shepard made less
use of the procedures trsiner than he might other-
wise have because of the difference in the panel
arrangement between the rainer and the early model
of the spacecraft which he flew. Shepard felt that
the computer attitude simulation provided an accu-
rate reproduction of the flight dynamics. Grissom
w as not able to make a good evaluation of this por-
tion of the simulation due to the malfunction of
the control system on his fight.
Shepard stressed the importance of accurate tim-
ing of events in the procedures trainer, noting that
a small time inaccuracy had momentarily disturbed
him during the flight. Grissom suggested that where
possible, sound cues associated with mission events
should be added to the simulation.
Air-Lubricated Free-Altitude Trainer
Both pilots felt that the air-lubricated f
tude I ALFA I trainer, a moving-base trainei i
provides angular-acceleration cues as well as a sim-
ulation of both the window and periscope views of
the earth, was very good for developing skill in the
attitude control task. It was more valuable to Gris-
som since the spacecraft he flew had the centerline
window. The angular response of the ALFA trainer
appeared to be accurate to Shepard and he felt that
this trainer was a necessarv addition to the fixed-
base training. As already noted. Astronaut Gris-
som fell that more practice in the ALFA trainer
with the pilot using the window reference would
have been desirable. He felt that the horizon sim-
ulation which, at present, is only an illuminated
band should be improved. Both pilots reported
that the simulated periscope view employing a pro-
jected earth map was very valuable.
Centrifuge
Hoth pilots felt that the centrifuge provided val-
uable training for launch and reentry periods.
Shepard reported that simulated accelerations of
the centrifuge during retrofiring were far more
jerky and upsetting than those occurring during the
flight. ". . . which were very smooth.7' Grissom
agreed that the flight accelerations were smc
he felt that the centrifuge simulations were
difficult than the flight. The centrifuge had pre-
pared him for a slight momentary vertigo sensation
which he experienced just after cutoff of the launch-
vehicle engine.
Participation in Spacecraft Checkout Activities at the
Launch Site
Both pilots felt that this portion of their prepara-
tion was particularly essential. During this period,
they were able to familiarize themselves with the
unique features of the actual spacecraft they were to
fly. Grissom summed up the value of this training
as follows: 'Tt is good to get into the flight capsule
[spacecraft] a number of times: then on launch dav.
you have no feeling of sitting on top of a booster
[launch vehicle] ready for launch. You feel as if
you were back in the checkout hangar — this is home,
the surroundings are familiar, you are at ease. You
cannot achiev e this feeling of familiarity in the pro-
cedures trainer because there are inevitably many
small differences between the simulator and the
capsule [spacecraft]."'
40
APPENDIX
Air-Ground Communications for MR— 4-
The following table gives a verbatim transcrip-
tion of the communications between the spacecraft
and the ground during the MR— 4 flight. The call
signs listed in the second column identify different
elements of the operation. The spacecraft is iden-
tified as "Rell 7" for Liberty Bell 7. The astronaut
communicator in the Blockhouse is identified as
"Stony. '"(Jap Com'' is the astronaut communi-
cator in the Mercury Control Center. "Chase" is an
astronaut in an F— 106 airplane. ''ATS ' stands for
the '"Atlantic Ocean Ship." a Mercury range station
aboard a ship which had been moved in close to
the landing area for this flight. ''Hunt Club " is the
designation given to the recovery helicopters.
"Card File" is the designation of a radio-relay air-
plane which relayed the spacecraft communications
to the Mercury Control Center.
( jtm muni-
ration
numluT
Cuiwnitni-
entur
S t < 1 1 1 y
Bell 7
( ."ap ( loin
Bell 7
( lap (
Bell 7
Time,
0:01
0:0.1
0:08
0:1 1
0:18
0:20
0:21. 5
0:28
Trans-
mission
dura-
tion,
sec
1
t. .>
3
1. 5
2. 5
L
I. 5
8. 5
( 'ap ( 'om
0:36. 5
2. 5
t
Hell 7
0:39
■3
0)
0:5 J
6.5
5
licll 7
1 :01.5
6.5
1 :08.5
0. 5
< 'ap ( !om
1:09
1
0
Hell :
1:10
0. 5
( iap ( ]oiii
1:11
Bell 7
1:13
9. 5
H
liell 7
1:23
0. 5
(.om
1:23.5
0. 5
<1
Bell 7
1:24
1. 5
(.ap Com
1:26
3
10
Bell 7
1:29
1. 5
1:31
15. 5
( lap (.om
1 :46.5
3
1 1
Bell 7
1:49.5
3
1:56
18. 5
1 ( Jonimuiiicator uniden
lified.
(_A>mmu!iication
1 if t -off.
Ah, Roger. This is Liberty Bell 7. The clock is operating.
I, oud and clear, Jose, don't cry too much.
Oke-<ioke.
OK, it's a nice ride up to now.
Lnud and clear.
Roger.
OK. The fuel is go; about l'a g's; cabin pressure is just coming off
the peg: the (h is go; we have 26 amps.
Roger. Pitch [attitude] 88 [degrees], the trajectory is good.
Roger, looks good here.
OK, there. We're starting to pick up a little bit of the noise and
vibration: not bad, though, at all. 50 sees., more vibration.
OK. The fuel is go; l'i g's; cabin is 8 [psi]: the 0j is go; 27 amps.
\nd [Rest of communication not received.]
Pitch is |Rest of communicat ion not received.]
l[gl, 5'g] |Rest of communication not received.!
Pitch [atlitudcj >s 77 [degrees]; trajectory is go.
Roger. Cabin pressure is still about 6 [psi[ and dropping slightly.
Looks like she's going to hold about 5.5 [psi].
Eh |Rest of communication not received.]
Cabin [Rest of communication not received. |
Believe me, Oi is go.
Cabin pressure holding 5.5 [psi!.
Roger, roger.
This is Liberty Bell 7. Fuel is go; 2*2 g"#; cabin pressure 5.5: 02 is go;
main [hus[ 25 [volts], isolated — ah, isolated [bus! is 28 [volts1,
ft e are go.
Roger, Pilch |atlitutle] is 62 [degrees!; trajectory is go.
Roger. It looks good in here.
Everything is good; cabin pressure is holding; suit pressure is OK:
2 minutes and we got 4 g's; fuel is go: ah, feel the hand controller
move just a hair there: cabin pressure is holding, O2 is go; 25 amps.
41
Trans -
mission
C.ommun i- dura-
CfltlOll
C^Qnl fn tin I -
tlOJl .
number
rator
min:ser
sec
Cap Com
2:15
1. 5
12
Bell 7
2:16.5
0. 05
C*ip Com
2:17
1. 5
L3
Bell 7
2:23
2
Chase 1
2:24.5
1. 5
it
Bell 7
2:26
4
Cilp Colli
2:31.5
ft ^
\f. o
15
Bell 7
2:33
9. 5
Cap Com
2:42.5
4.5
16
Bell 7
2:47
13. 5
Cap Com
3:01
0. 5
17
Bell 7
3:02
8. 0
Cap Com
3:10.5
3.5
18
Bell 7
3:15.5
3
Cap Com
3:20.5
4
19
Bell 7
3:24.5
3
Cap Com
3:28
0.5
20
Bell 7
3:31
4
Cap Com
3:36
3
21
Bell 7
3:40.5
3
22
Bell 7
3:45
1.4
Cap Com
3:47.5
1. 5
lieil 4
1
24
Bell 7
3:51.5
4
Cap Com
3:57.5
2
25
Bell 7
3:59.5
2
26
Bell 7
4:02
12
Cap Com
4:15
3.5
27
Bell 7
4:18.5
5.5
Cap Com
4:25
1.5
28
Bell 7
4:29.5
Cap Com
4:30.5
1.5
(■)
4:33
4.5
29
Bell 7
4:37.5
3.5
Cap Com
4:42
2
30
Bell 7
4:44
4
Cap Com
4:48
3.5
31
Bell 7
4:52
4
Cap Com
4:57
3.5
32
Bell 7
5:01.5
2. 5
Cap Com
5:05
6
(')
Communicator imiden lifted.
Comm unication
Roger, we have go here.
And I see a star!
Stand by for cutoff.
There went the tower.
Roger, there went the tower, affirmative Chase.
Roger, squibs are off.
Roger.
There went posigrades, capsule has separated. We are at zero g and
turning around and the sun is really bright.
Roger, cap. sep. [capsule separation light] is green; turnaround has
started, manual handle out.
Oh boy! Manual handle is out; the sky is very black; the capsule is
coining around into orbit attitude; the roll is a little bit slow.
Roger.
I haven't seen a booster anyplace. OK, rate command is coming on.
I'm in orbit attitude, I'm pitching up. OK, 40 [Rest of communi-
cation not received.] Wait, I've lost some roll here someplace.
Roger, rate command is coming on. You're trying manual pilch.
OK, I got roll back. OK, I'm at 24 [degrees] in pitch.
Roger, your IP [impact point] is right on, Gus, right on.
OK. I'm having a little trouble with rate, ah, with the Miami, il con-
trol.
Roger.
If I can get her stabilized here, all axes are working all right.
Roger. Understand manual control is good.
Roger, it's — it's sort of sluggish, more than 1 expected.
OK, I'm yawing.
Roger, yaw.
Left, ah.
OK, coming back in yaw. I'm a little bit late there,
Roger. Reading you loud and clear, Gus.
Lot of stuff — there's a lot of stuff floating around up here.
OK, I'm going to skip the yaw [maneuver], ah, or [rather the] roll
[maneuver] because I'm a little bit late and I'm going to try this
rough yaw maneuver. About all I can really see is clouds. I
haven't seen any land anyplace yet.
Roger, you're on the window. Are you trying a yaw maneuver?
I'm trying the yaw maneuver and I'm on the window. It's such a
fascinating view out the window you just ean't help but look out
that way.
I understand.
You su, ah, really. There I see the coast, I see.
4 + 30 [elapsed time since launch] Gus.
4 + 30 [elapsed time since launch] he's looking out the window, A— OK.
I can see the coast but I can't identify anything.
Roger, 4-}-30 [elapsed time since launch] Gus.
OK, let me get back here to retro attitude, retro sequence has started.
Roger, retro sequence has started. Go to retro attitude.
Right, we'll see if I'm in bad, not in very good shape here.
Got 15 seconds, plenty of time, I'll give you a mark at 5:10 [elapsed
time since launch],
OK, retro attitude [light] is still green.
Retros on my- mark, 3, 2, 1, murk.
He's in limits. [Falls in the middle of last Cap Com communication.]
42
Trans-
_ mission
( >ji- dura-
Communi-
Time,
Hon,
T
cator
min:sec
sec
33
Bell 7
5:11,5
^ )
5:12
1
(jflp Coin
5:13.5
1
31
Bell 7
5:19
o
Cap Com
5:21
2. 5
lioll 7
5:23.5
X
Bell 7
5:25.5
2. 5
Cap Com
3
1 T
O i
Hell 7
5:33.5
38
Bell 7
5:36
1.5
Cap Com
5:38
3
39
Bell 7
5:41
3
Cap Com
5:11.5
1.5
5:52
6. S
0)
K)
Bell 7
6:08
18
Cap Coin
6:05
6
ll
Bell 7
6:34
3. 5
( jap Coin
6:38
1. 5
1-1
1-1*11 "
6:41
3. 5
Cap Coin
6: 17
4. 5
Bell 7
6:51.5
1
Cap Corn
6:56.5
3.5
i4
Bell 7
7:00.5
3
15
Bell 7
7:05.5
0. 5
l" '1 T k I fiTTI
7:07
2. 5
16
Bell 7
7:09.5
1
1 Oft 1 sim
7:14.5
;j
C- *i p t^oni
7:27
2. 5
1 i
Bell 7
7:30
3. 5
Csp Coiti
7:33.5
-K>
Bell 7
7:37
2
Ilt.ll 7
3
— . j
Cap Com
7:57
1
50
Bell 7
8:03.5
.}
Cup Co ni
8:09
1 . 5
51
Bell 7
8:11
5
52
Bell 7
8:17
1.5
53
Bell 7
8:19
1 1. 5
Cap Com
8:32
2
51
Bell 7
8:31.5
3
Cap Com
8:38.5
1.5
55
Hell 7
8:42
7. 5
Cap Com
8:49.5
2.5
1 Communicator unidentified.
Communication
OK, there's 1 firing, there's 1 firing.
Retro 1. [Cuts out Bell 7.]
Roger, retro I.
There's 2 firing, nice little boost. There went 3.
Roger, 3, all retros are fireil.
Roger, roger.
OK, yell, they're fired out right there.
Roger, retrojettison armed.
Retrojetlison is armed, retrojettison is armed, going to rate com-
mand.
OK, I'm going to switch.
Roger. Understand manual fuel handle is in.
Manual fuel handle is in, mark, going to HF.
Roger, HF.
Liberty Bell 7, this is Cap Com on HF, 1, 2, 3, 4, 5. How do you
read [Bell] 7?
I got you.
. . . here, do you read me, do you read me on HF? . . . Going
back to U [UHF] . . . [received by ATS ship]. Boy is that . . .
Retro, I'm back on UHF and, ah, and the jett — the retros have
jettisoned. Now I can see the Cape and, oh boy, that's some sight.
I can't see too much.
This is Cap Com on HF, 1, 2, 3, 4, 5. How do you read [Bell] 7?
Roger, I am on UHF high, do you read me?
Roger, reading you loud and clear UHF high, can you confirm retro-
jettison?
OK, periscope is retracting, going to reentry attitude.
Roger. Retros have jettisoned, scope has retracted, you're going to
reentry attitude.
Affirmative.
Bell 7 from Cap Com, your IF [impact point] is right on.
Roger, I'm in reentry attitude.
Ah.
Roger, how does it look out the window now?
Ah, the sun is coming in and so all I can see really is just, ah, just
darkness, the sky is very black.
Roger, you have some more time to look if you like.
[Bell] 7 from Cap Com, how do you feel up there?
1 feci very good, auto fuel is 90 [percent], manual is 50 [percent],
Roger, 0.05g in 10 [seconds .
OK.
OK, everything is very good, ah.
I got 0.05g [light] and roll rate has started.
Roger.
Got a pitch rate in here, OK, g's are starting lo build.
Roger, reading you loud and clear.
Roger, g's are building, we're up to 6[g[.
There's 9[gl.
There's about 10[g|; the handle is out from under it; here I got a little
pitch rate coming back down through 7[gl-
Roger, still sound good.
OK, the altimeter is active at 65 [thousand feet]. There's 60 [thou-
sand feet].
Roger, 65,000.
OK, I'm getting some contrails, evidently shock wave, 50,000 feet;
I'm feeling good. I'm very good, everything is fine.
Roger, 50,000.
43
Trans-
mission
Communi- dura-
cation
i'.oiuniiini -
Time,
tion,
•umlter
cator
min: sec
see
56
Hell 7
8:52
1. 5
Cap Com
8:54
2.5
57
Hell i
9:00.5
3
58
Bell 7
9:07
2
59
Bell 7
9:19
7
Cap Coin
9:24
2. 5
«
60
Bell 7
9:28
2
61
Bell 7
9:36.5
2.5
62
Bell 7
9:41.5
4. 5
Cap Com
9:45
4
63
Bell 7
9:49.5
13. 5
Cap Com
64
Bell 7
10:05.5
2
Cap Com
65
Bell 7
10:11
25
(')
66
Bell 7
10:40.5
3
Cap Com
ATS
67
Bell 7
Card File 23
68
Bell 7
10:52
4
ATS
69
Bell 7
11:12
8
ATS
70
Bell 7
11:28
4
ATS
71
Bell 7
11:42.5
2. 5
ATS
72
Bell 7
11:47.5
3
73
Bell 7
12:04
5
74
Bell 7
12:15
1. 5
75
Bell 7
12:35
16
ATS
76
Bell 7
13:04
2
Card File 23
Communicator unident ified.
Communieation
45,000, do you still read?
Affirmative. Still reading you. You sound good.
OK, 40,000 feet, do you read?
35,000 feet, if you read me,
30,000 feet, everything is good, everything is good.
Bell 7, this is Cap Com. Hon .... [Rest of communieation not
received.]
Cape, do you read?
25,000 feet.
Approaching drogue chute attitude.
There's the drogue chute. The periscope has extended.
This is . . . we have a green drogue [light] here, 7 how do vou read?
OK, we're coming down to 15,000 feet, if anyone reads. W e re on
emergency flow rate, can see out the periscope OK. The drogue
chute is good.
Roger, understand drogue is good, the periscope is out.
There's 13,000 feet.
Roger.
There goes the main chute: it's reefed; main chute is good; main chute
is good; rate of descent coming down, coming down to — there's 40
feet per second, 30 feel per, 32 feet per second on the main chute,
and the landing hag is out green.
Ah, it's better than it was, Chuck.
Hello, does anybody read Liberty Bell, main chute is good, landing
bag [light] is on green.
And the landing bag [light] is on green.
Liberty Bell 7, Liberty Bell 7, this is Atlantic Ship Cap Com. Read
you loud and clear. Our telemetry confirms your events. Over.
Ah, roger, is anyone reading Libertv Bell 7? Over.
Roger, Liberty Bell 7, reading you loud and clear. This is C
23. Over.
Atlantic Ship Cap Com, this is Liberty Bell 7, how do you nan „ie?
Over.
Read you loud and clear, loud and clear. Over. Libertv I5el! 7,
Liberty Bell 7, this is Atlantic Ship Cap Com. How do you read me?
Over.
Atlantic Ship Cap Com, this is Liberty Bell 7, I read you loud and
clear. How, me? Over.
Roger, Bell 7, read you loud and clear, your status looks good, your
systems look good, we confirm your events. Over.
Ah, roger, and confirm the fuel has dumped. Over.
Roger, confirm again, confirm again, has your auto fuel dumped?
Over.
Auto fuel and manual fuel has dumped.
Roger, roger.
And I'm in the process of putting the pins back in the door at this time.
OK, I'm passing down through 6,000 feet, everything is good, ah.
I'm going to open my face plate.
Hello, I can't get one; 1 can't get one door pin back in. I've tried
and tried and I can't get it back in. And I'm coming, ATS, I'm
passing through 5,000 feet and I don't think I have one of the door
pins in
Roger, Bell 7, roger.
Do you have any word from the recovery troops?
Liberty Bell 7, this is Card File 23; we are heading directly toward
you.
44
Trans-
11-
Communi-
t c.ator
Time,
mi n: sec
mission
tion,
sec
Bell 7
13:18
4
ATS
Bell 7
13:33
13
ATS
Bell 7
13:49
45
80
81
82
83
84
5
16
ATS
Bell 7
ATS
(')
Bell 7
0)
Hell 7
(l)
Bell 7
Bell 7
ATS
Bell 7
Hunt Club 1
Card File 9
Hell 7
(')
(')
Hunt Club 1
Iiell 7
Hunt Club 1
Bell 7
Bel! 7
Hunt Club 1
Bell 7
14:39
14:54
16:35
18:07
18:16
18:23
18:32.5
33
8. 5
Hunt Club 1
Communicator unidentified.
Communication
ATS, this is Cap — this is Liberty Bell 7. Do you have any word
from the recovery troops?
Negative, Bell 7, negative. Do you have any transmission to MCC
[Mercury Control Center ? Over.
Ah, roger, you might make a note that there is one small hole in ray
chute. It looks like it's about 6 inches by 6 inches — it's a sort of
a — actually it's a triangular rip, I guess.
Ah, roger, roger.
I'm passing through 3,000 feet, and all the fuses are in flight condi-
tions; ASCS is normal, auto: we're on rate command; gyros are
normal; auto retrojetlison is armed; squibs are armed also. Four
fuel handles are in; decompress and reeompress are in; retro delay is
normal; retroheat is off, cabin lights are both, T\I [telemeter] is on.
Rescue aids is auto; landing bag is auto; retract scope is auto;
retroattitude is auto. All ihe three, five pull rings are in. Going
down through some clouds to 2,000 feet. ATS, I'm at 2,000 feet;
everything is normal.
Roger, Bell 7, what is your rate of descent again? Over.
The rate of descent is varying between 28 and 30 feet per second.
Ah, roger, roger, and once again verify your fuel has dumped. Over.
Seven ahead at bearing 020. Over.
OK. My max g was about 10.2; altimeter is 1,000 [feet]; cabin
pressure is coming toward 15 [pai],
^ e'll make up.
Temperature is 90 [°F].
We'll make up an eye rep.
Coolant quantity is 30 [percent]; temperature is 68 [°F]: pressure is
14 [psi[; main 02 is 60 [percent]; norma] is, main is 60 [percent];
emergency is 100 [percent]: suit fan is normal; cabin fan is normal.
We have 21 amps, and I'm getting ready for impact here.
Can see the water coming right on up.
Liberty Bell 7, Liberty Bell 7, this is Atlantic Cap Com, do you read
me? Over.
OK, does anyone read Liberty Bell 7? Over.
Liberty Bell 7, Hunt Club 1 is now 2 miles southwest you.
Liberty Bell 7 this 9 Card File. We have your entry into the water.
Will be over you in just about 30 seconds.
Roger, my condition is good; OK the capsule is floating, slowly coming
vertical, have actuated the rescue aids. The reserve chute has
jettisoned, in fact I can sec it in the water, and the whip antenna
should be up.
Hunt Club, did you copy?
OK, Hunt Club, this is . . . Don't forget the antenna.
This is Hunt Club, say again.
Hunt Club, this is Liberty Bell 7. My antenna should be up.
This is Hunt Club 1 . . . your antenna is erected.
Ah, roger.
OK, give me how much longer it'll be before you gel here.
This is Hunt Club 1, we are in orbit now at this time, around the
capsule.
Roger, give me about another 5 minutes here, to mark these switch
positions here, before I give you a call to come in and hook on.
Are you ready to come in and hook on anytime?
Hunt Club 1, roger we are ready anytime you are.
Cum mil ni-
cation
numher
87
8K
a*)
1)0
<)1
92
ti:s
04
Commuiii- Time,
catur ntin:sec
Bell 7 18: H
Hunt Club 1
Card Kilt- 9
Hunt Club 1
Bell 7 20:1:">
Hunt Club 1
Hell 7
Hunt Club 1
Cap Com
( lap Com
Card File 9
Hunt Club 1
Card File 9
Hunt Club 1
Hunt Club 3
Card File 9
liell 7
Hum Club 1
Hell 7
Hum Club 1
liell 7
Hunt Club 1
Bell 7
Hum Club I
Hell 7
.20: 26
24:03
2.",: 19.,",
25:30
25:12
25:52.5
26:09
mission
dura-
tion ,
sec
1. 5
Communication
OK, give me about another 3 or 4 minutes here to take these switch
positions, then J 11 be ready for you.
1, wilco.
Hey Hunt Clubs, Card File, Card File 9, I'll stand by to escort sou
back as soon as you lift out. 1 keep other aircraft at at least 2.000
feet.
Ah, liell 7 this is Hunt Club 1.
Go, go ahead Hunt Club f .
Roger, this is I, observe something, possibly the canister in the water
along side capsule. Will we be interfering with any I'M |telerrielr_v j
if we come down and lake a look at it/
Negative, not at all, Fill just going to put the rest of thi> stuff on tape
and then I'll be ready for vou, in just about 2 more minutes, I would
say.
1 roger.
Liberty Bell 7, Cap Com at the Cape on a test eouril. Over.
Liberty bell 7, Cape Cap Com on a test count. Over.
Any Hunt Club, this is 9 Card bile.
Station calling Hunt Club, say again.
This is Niner Cardfile, there's an object on a line in the water, ah. jus!
about 160 degrees. The N ASA people suspect it's the dye marker
that didn't activate: ah, say it's about, ah, /4 of a mile out from the
capsule. Ah, after the lift out, will you take a check on il? Over.
Ah, this is Hunt Club 1, roger. will have Hunt Club 3 check ul ibis
time, you copy 3.
Hunt Club f, believe he said 'U of a mile?
This is 9 Card, that is affirmative.
This is Liberty Hell
Are vou ready lor the
power down and h.
all when we're readv
OK, Hunt Club,
pickup?
This is Hunt Club 1: this is allirmative.
OK, latch on, then give me a call and 1
hatch, OK?
This is Hunt Club L, roger, will give vou a call when we're ready l<
you to blow.
Roger, I've uti[ lugged my suit so I'm kinda warm now so.
1 , roger.
Now if vou tell me to. ah, you're ready lor me to blow, I II have to
take my helmet off, power down, and then blow the hatch.
1, roger, and when vou blow the hatch, the collar will already be down
there waiting for vou, and we're turning base at this lime.
Ah, roger.
No further communications were received as a result of the emergency egress required by the failure
of the side hatch.
Reference
1. .Slaytos, Donald K.: Pilot Training and Pre flight Preparation, Proc. Conf. on Results of the First U.S. Manned
Suborbital Space Flight, NASA, Nat. Inst. Health, and Nat. Acad. Sri., June 6. 1961, pp. 53-60.
46
7. PILOT'S FLIGHT REPORT
Bv Virgil I. Gkissom. Astronaut, NASA Manned Spacecraft Center
Introduction
The second Mercury manned flight was made on
J ul\ 21. l'Jol. The flight plan provided a ballistic
Irajertorv having a maximum altitude of 103 nauti-
cal mile?;, a range of 263 nautical miles, and a 5-
minute period of weightlessness.
The following is a chronological report on the
pilot's activities prior to. during, and after the flight.
Prenijrht
The preflight period is composed of two distinct
areas. The first is the training that has been in
progress for the past 21 j years and which is still in
progress. The second area, and the one that as-
sumes the most importance as launch date ap-
proaches, is the participation in the day-to-day
engineering and testing that applies directly to the
spacecraft that is to be flown.
Over the past 2 years, a great deal of information
has been published about the astronaut training pro-
gram and the program has been previously described
in reference 1. In the present paper. I intend to
comment on onlv three trainers which 1 feel have
been of the greatest value in preparing me for this
flight.
The first trainer that has proven most valuable is
the Mercurv procedures trainer w hich is a fixed-
based computer-operated flight simulator. There
are two of these trainers i fig. 7-1). one at the
Figuke 7-1. Procedures trainf-r.
47
NASA-Langley Air Force Base, Va., and one at
the Mercury Control Certer. Cape Canaveral, Fla.
These procedures traineis have been used contin-
uously throughout the program to learn the system
operations, to learn emergency operating techniques
during system malfunctions, to learn control tech-
niques, and to develop cperational procedures be-
tween pilot and ground personnel.
During the period preceding the launch, the
trainers were used to finalize the flight plan and to
gain a high degree of proficiency in flying the mis-
sion profile (fig. 7-2). First, the systems to be
checked specifically bv the pilot were determined.
These were to be the manual proportional control
system; the rate command control system; attitude
control with instruments as a reference: attitude
control with the earth-sky horizon as a reference;
the UHF, HF, and emergency voice communications
systems; and the manual retrofire override. The
procedures trainer was then used to establish an
orderly sequence of acconplishing these tasks. The
pilot functions were tried and modified a great num-
ber of times before a satisfactory sequence was
determined. After the flight plan was established,
it was practiced until each phase and time was
memorized. During this phase of training, there
was a tendency to add more tasks to the mission
flight plan as proficiency was gained. Even though
the MR-4 flight plan (table 7-1) contained less pilot
functions than the MR— 3 flight plan, I found that
the view out the window, which cannot be simulated,
distracted me from the less important tasks and
often caused me to fall bebind the planned program.
The only time this distraction concerned me was
prior to retrofire; at other times, I felt that 1 g
out the window was of greater importance the
of the planned menial tasks. In spite of this pleooant
distraction, all tasks were accomplished with the
exception of visual control of retrofire.
The second trainer that was of great value and one
that I wish had been more readily available prior to
launch was the air-lubricated free-attitude (ALFA)
trainer at the NASA-Langley Air Force Base. Va.
(fig. 7-3). This trainer provided the only training
in visual control of the spacecraft. I had intended
to use the earth-sky horizon as my primary means
of attitude control and had spent a number of hours
on the ALFA trainer practicing retrofire using the
horizon as a reference. Because of the rush of
events at Cape Canaveral during the 2 weeks prior
to launch, I was unable to use this trainer. I felt
this probably had some bearing on my instinctive
switch to instruments for retrofire during the flight,
instead of using the horizon as a reference.
The third training device that was of great value
was the Johnsville human centrifuge. With this de-
vice, we learned to control the spacecraft during the
accelerations imposed by launch and reentry and
learned muscle control to aid blood circulation and
respiration in the acceleration environment. The
acceleration buildup during the flight was con?' — r-
ably smoother than that experienced on the
fuge and probably for this reason and for ot. .4
psychological reasons, the g-forces were much easier
to withstand during the flight than during the train-
ing missions.
REFEEENCE - W!N:3EC
ALT. APFRCX. ICii.SN.M.
AT 34:46 RET3C~IRE SEQUENCE IS INITIATED
NOR^LAL CREITING ATTH UDE
ATi itud- p?,cc-f.av2*:;kg
BY \SCSt COUNTER CLOCK.
'.VIS ■ YAW MANEUVER
L MINUTE AFTER ESTRONE STARTS
RETRC PACKAGE JETTISONED
c'JSKC AFTER RETRO PACKAGE
:ETTI3C-\, PERISCOPE 13 RETRACTED
20 ,±7" ANGLE- CF- ATTACK.
AFTER . 2iqt STEADY RCLL CF
:C'a TO 12 PER SECOND
is sec popiod of rate damping
V_ C2:3L SPACECRAFT SEPARATION
A-ND P iP.ISOGPl EXTENDED
32:25 CUTCFE, TO' VSR SEPARATION
PERIOD CF WEIGHTLESSNESS APPPOJi. : Mitt.
TOTAL FLIGHT TIME APPRCX. 1= MIN.
CPS?.' PARACHUTES
CO 12= -5C
RANGE, NAUTICAL WILES
MAX TANGENTIAL
LOAD FACTOR llq
06:20
EXTEND PERISCOPE AGAIN
Figure 7-2. Mission profile.
48
Figure 7-3. ALFA trainer.
One other phenomenon that was experienced on
the centrifuge proved to be of great value during
the flight. Quite often, as the centrifuge changed
rapidly from a high g-level to a low or 1 g level,
a false tumbling sensation was encountered. This
became a common and expected sensation and when
the same thing occurred at launch vehicle cutoff, it
was in no way disturbing, A quick glance at my
instruments convinced me that I. indeed, was not
tumbling.
The pilot's confidence comes from all of the fore-
going training methods and from many other areas,
but the real confidence comes from participation in
the day-to-day engineering decisions and testing that
occur during the prefligh: checkout at Cape Canav-
eral. It was during thh time that I learned the
particular idiosyncrasies of the spacecraft that I
was to fly. A great deal of time had already been
spent in learning both normal and emergency sys-
tem operations. But during the testing at the pre-
flight complex and at the launching pad, I learned
all the differences between this spacecraft and the
simulator that had been u:;ed for training. I learned
the various noises and vibrations that are connected
with the operation of the systems. This was the
time that I really begar to feel at home in this
cockpit. This training was very beneficial on launch
day because I felt that I knew this spacecraft and
what it would do. and h.rving spent so much time
in the cockpit I felt it was normal to be there.
As a group, we astrcnauts feel that after the
spacecraft arrives at the Cape, our time is best spent
in participating in spacecraft activities. This causes
some conflict in training, since predicting the time
test runs of the preflight checkouts will start or end
is a mystic art that is mderstood by few and is
unreliable at its best. Qtite frequently this causes
training sessions to be canceled or delayed, but it
should he of no great concern since most of the
training has been accomplished prior to this time.
The use of the trainers luring this period is pri-
marily to keep performance at a peak and the time
required will vary from pilot to pilot.
At the time the spacecraft is moved from the pre-
flight complex to the launching pad. practically all
training stops. From this, time on, I was at the pad
full time participating in or observing every test
that was made on the spacecraft — launch-vehicle
combination. Here, I became familiar with the
launch procedure and grew to know and respect the
launch crew. I gained confidence in their profes-
sional approach to and execution of the pre1 -h
tests.
The Flight
On the day of the flight, I followed the following
schedule :
Event a.m. e.s.t.
Awakened | 1:10
Breakfast 1:25
Physical examination 1:55
Sensors attached ; 2:25
Suited up j 2:35
Suit pressure check I 3:05
Entered transfer van ! 3:30 i
Arrived at pad , 3:55 ,
Manned the spacecraft | 3:58
Launched ' 7:20 t
As can be seen, 6 hours and 10 minutes elapsed
from the time I was awakened until launch. This
time is approximately evenly divided between activi-
ties prior to my reaching the pad and time I spent
at the pad. In this case, we were planning on a
launch at 6:00 a.m. e.s.t., but it will probably always
be normal to expect some holds that cannot be -! e-
dicted. While this time element appears to
cessive. we can find no way to reduce it belo, j,
minimum at the present. Efforts are still continu-
ing to reduce the precountdow n time so that the pilot
will not have had an almost full working day prior
to lift-off.
After insertion in the spacecraft, the launch
countdown proceeded smoothly and on schedule
until T — 45 minutes when a hold w as called to install
a misalined bolt in the egress hatch.
After a hold of 30 minutes, the countdown was
resumed and proceeded to T — .10 minutes when a
brief hold was called to turn off the pad searchlights.
By this time, it was daylight: and the lights, which
cause interference with launch-vehicle telemetry,
w ere no longer needed.
One more hold was called at T— 15 minutes to
await better cloud conditions because the long focal
length cameras would not have been able to obtain
proper coverage through the existing overcast.
After holding for 41 minutes, the count was re-
sumed and proceeded smoothly to lift-off at 7 :20
a.m., e.s.t.
50
The communications and flow of information
pr;-- to lift-off were very good. After participating
prelaunch test and the cancellation 2 days
p. uslv. I was very familiar with the countdown
and knew exactly what was going on at all times.
As the Blockhouse Capsule Communicator (Cap
Com I called ignition, I felt the launch vehicle start
to vihrate and could hear the engines start. Just
seconds after this, the elapsed-time clock started and
the Mercury Control Center Cap Com confirmed
lift-off. At that time, 1 punched the Time Zero
Override, started the stopwatch function on the
spacecraft clock, and reported that the elapsed-time
clock had started.
The powered flight portion of the mission was
in general very smooth. A low-order vibration
started at approximately T + 50 seconds, but it did
not develop above a low level and w-as undetectable
after about T + 70 seconds. This vibration was in
no wav disturbing and it did not cause interference
in either communications or vision. The magnitude
of the accelerations corresponds well to the launch
simulations on the centrifuge, but the onset was
much smoother.
Communications throughout the powered flight
were satisfactory. The VOX ( voice operated relay)
was used for pilot transmissions instead of the push-
\ button. The noise level was never high
a at any time to key the transmitter. Each
standard report was made on time and there was
never any requirement for myself or the Cap Com
to repeat any transmission.
Vision out the w indow w as good at all times during
launch. As viewed from the pad. the sky was its
normal light blue: but as the altitude increased, the
sky became a darker and darker blue until approxi-
mately 2 minutes after lift-off, which corresponds
to an altitude of approximately 100.000 feet, the
sky rapidlv changed to an absolute black. At this
time. I saw what appeared to be one rather faint
star in the center of the w indow I fig. 7-4 ). ft was
about equal in brightness to Polaris. Later, it was
determined that this was the planet Venus whose
brightness is equal to a star of magnitude of —3.
Launch-vehicle engine cutoff was sudden and I
could not sense any tail-off of the launch vehicle.
1 did feel, as I described earlier, a very brief tum-
bling sensation. The firing of the escape-tower
clamp ring and escape rocket is quite audible and I
could see the escape rocket motor and tower through-
out its tail-off burning phase and for what seemed like
quite some time after that climbing off to my right.
Actually. I think 1 was still watching the tower at
the time the posigrade rockets fired, which occured
10 seconds after cutoff. The tower was still defin-
able as a long, slender object against the black sky
at this time.
* First-order s:ar
* Secor.d-crdsr star
* Triird-order ^t.ar
Figure 7-4. Approximate view of stars through centerline
window.
The posigrade firing is a very audible bang and
a definite kick, producing a deceleration of approxi-
mately lg. Prior to this time, the spacecraft was
quite stable with no apparent motion, As the posi-
grade rockets separated the spacecraft from the
launch vehicle, the spacecraft angular motions and
angular accelerations were quite apparent. Space-
craft damping v hich was to begin immediately after
separation was apparently satisfactory, although
I cannot really report on the magnitude of any an-
gular rates caused by posigrade firing.
The spacecraft turnaround to retrofire attitude is
quite a weird maneuver to ride through. At first. I
thought the spacecraft might be tumbling out of con-
trol. A quick check of the instruments indicated that
turnaround was proceeding much as those experi-
enced on the procedures trainer, with the expection
of roll attitude which appeared to be very slow and
behind the schedule that I was expecting.
As the turnaround started, I could see a bright
shaft of light, similar to the sun shining into a
blackened room, start to move from my lower left up
across my torso. Even though I knew the window
reduces light transmissions equivalent to the earth s
atmosphere, I was concerned that it might shine
directly into my eyes and blind me. The light moved
across my torso and disappeared completely.
51
A quick look through the periscope after it ex-
tended did not provide m; with any useful informa-
tion. I was unable to see land, only clouds and the
ocean.
The view through the v.indow became quite spec-
tacular as the horizon came into view. The sight
was truly breathtaking. The earth was very bright,
the sky was black, and the curvature of the earth was
quite prominent. Between the earth and sky. there
was a border which startad at the earth as a light
blue and became increasingly darker with altitude.
There was a transition reg ion betw een the dark blue
and the black sky that is best described as a fuzzy
gray area. This is a very narrow band, but there is
no sharp transition from blue to black. The whole
border appeared to be uniform in height over the
approximately 1,000 miles of horizon that was visible
to me.
The earth itself was very bright. The only land-
mark I was able to identi fy during the first portion
of the weightlessness period was the Gulf of Mexico
coastline between Apalachicola, Fla., and Mobile,
Ala. (fig. 7-5). The cloud coverage was quite ex-
tensive and the curvature of this portion of the coast
was very difficult to distinguish. The water and land
masses were both a hazy blue, with the land being
Ficire 7-5. Approximate viev of earth through centerline
window.
somewhat darker. There was a frontal system south
of this area that was clearly defined.
One other section of the Florida coast ca ">
view during the left yaw maneuver, but it a
small section of beach with no identifiable landmarks.
The spacecraft automatic stabilization and control
system (ASCSl had made the turnaround maneuver
from the position on the launch vehicle to retrofire
attitude. The pitch and yaw axes stabilized with
only a moderate amount of overshoot as predicted,
but the roll attitude was still being programed and
was off by approximately 15° when I switched from
the autopilot to the manual proportional control sys-
tem. The switchover occurred 10 seconds later
than planned to give the ASCS more time to stabilize
the spacecraft. At this point, I realized I would
have to hurry my programed pitch, yaw, and roll
maneuvers. I tried to hurry the pitch-up maneuver ;
I controlled the roll attitude back within limits, but
the view out the window had distracted me, resulting
in an overshoot in pitch. This put me behind in
my schedule even more. I hit the planned yaw rate
but overshot in yaw attitude again. 1 realized that
my time for control maneuvers was up and I decided
at this point to skip the planned roll maneuver, since
the roll axis had been exercised during the two pre-
vious maneuvers, and go immediately to the next
task.
This was the part of the flight to which I har
looking forward. There was a full minute th,
programed for observing the earth. My observa-
tions during this period have already been reported
in this paper, but the control task was quite easy
when only the horizon was used as a reference. The
task was somewhat complicated during this phase,
as a result of lack of yaw reference. This lack was
not a problem after retrofire when Cape Canaveral
came into view. I do not believe yaw attitude will
be a problem in orbital flight because there should
be ample time to pick adequate checkpoints; even
breaks in cloud formations would be sufficient.
The retrosequence started automatically and at
the time it started, I was slightly behind schedule.
At this point, I was working quite hard to get into a
good retrofire attitude so that I could fire the retro-
rockets manually. I received the countdown to fire
from Mercury Control Center Cap Com and fired
the retrorockets manually. The retrorockets, like
the escape rocket and posigrades, could be heard
quite clearly. The thrust buildup was rapid and
smooth. As the first retrorocket fired, I was look-
ing out the window and could see that a definite
52
yaw to the right was starting. I had planned to con-
tr ' i spacecraft attitude during retrofire by using
! izon as a reference; but as soon as the right
ya.. carted. I switched my reference to the flight in-
struments. I had been using instruments during my
retrofire practice for the 2 weeks prior to the launch
in the Cape Canaveral procedures trainer since the
activity at the Cape prevented the use of the ALFA
trainer located at the iV ASA-Langley Air Force
Base, Va. This probably explains the instinctive
switch to the flight instruments.
The retrofire difficulty was about equal to the
more severe cases that have been presented on the
procedures trainer.
Immediately after retrofire. Cape Canaveral came
into view, ft was quite easy to identify. The Ba-
nana and Indian Rivers were easy to distinguish and
the white beach all along the coast was quite prom-
inent. The colors that were the most prominent
were the blue of the ocean, the brownish-green of
the interior, and the white in between, which was
obviously the beach and surf. I could see the build-
ing area on Cape Canaveral. I do not recall being
able to distinguish individual buildings, but it yvas
obvious that it was an area where buildings and
structures had been erected.
Immediately after retrofire, the retro] ettison
switrh was placed in the armed position, and the
mode was switched to the rate command con-
i stem. I made a rapid check to ascertain that
the system yvas working in all axes and then 1
switched from the LHF transmitter to the HF trans-
mitter.
This one attempt to communicate on HF was un-
successful. At approximately peak altitude, the HF
transmitter was turned on and the LHF transmitter
was turned off. All three receivers — LHF. HF, and
emergency voice — were on continuously. Immedi-
ately after I reported switching to HF, the Mercury
Control Center started transmitting to me on HF
only. I did not receive any transmission during this
period. After allowing the HF transmitter approx-
imately 10 seconds to warm up. I transmitted but
received no acknowledgement that I was being re-
ceived. Actually, the Atlantic Ship telemetry vessel
located in the landing area and the Grand Bahama
Island did receive my HF transmissions. Prior to
the flight, both stations had been instructed not to
transmit on the assigned frequencies unless they
were called by the pilot. After switching back to
the I HF transmitter. I received a call on the emer-
gency voice that was loud and clear. UHF commu-
nications were satisfactory throughout the flight. I
was in continuous contact with some facility at all
times, with the exception of a brief period on HF.
Even though all communications equipment oper-
ated properly, I felt that I was hurrying all trans-
missions too much. All of the sights, sounds, and
events were of such importance that I felt compelled
to talk of everything at once. It was a difficult
choice to decide what yvas the most important to
report at any one time. I wanted as much as pos-
sible recorded so that I would not have to rely on my
memory so much for later reporting.
As previously mentioned, the control mode was
switched from manual proportional to rate com-
mand immediately after retrofire. The procedures
trainer simulation in this system seems to be
slightly more difficult than the actual case. I found
attitudes were easy to maintain and rates were no
problem. The rate command system yvas much
easier to fly than the manual proportional system.
The reverse is normally true on the trainer. The
sluggish roll system was probably complicating the
control task during the manual proportional control
phase of the flight, while roll accelerations appeared
to be normal on the rate command system.
The rate command control system was used after
retrofire and throughout the reentry phase of the
flight. At the zero rate command position, the stick
was centered. This system had a deadband of ±3
deg 'sec. Our experience on the procedures trainer
had indicated that this system yvas more difficult to
fly than the manual proportional control system.
This was not the case during this flight. Zero rates
and flight attitudes were easy to maintain. The rec-
ords do indicate that an excessive amount of fuel
was expended during this period. Approximately
15 percent of the manual fuel supply was used dur-
ing the 2 minutes the system was operating. A major
portion of the 2 -minute period was during the re-
entry when thrusters were operating almost con-
tinuously to dampen the reentrv oscillations.
The 0.05g telelight illuminated on schedule and
shortly thereafter I reported g's starting to build.
I checked the accelerometer and the g-level was
something less than Ig at this time. The next time I
reported, I was at 6g and I continued to report and
function throughout the high-g portion of the flight.
The spacecraft rates increased during the reentry,
indicating that the spacecraft was oscillating in both
vaw and pitch. I made a few control inputs at this
time, but I could not see any effects on the rates, so
I decided just to ride out the oscillations. The pitch
53
rate needle was oscillating full scale at a rapid rate
of ±6 deg/sec during tiis time and the vaiv rate
began oscillating full sea e slightly later than pitch.
At no time were these oscillations noticeable inside
the spacecraft.
During this phase of reentry and until main para-
chute deployment, there is a noticeable roar and a
mild buffeting of the spacecraft. This is probably
the noise of a blunt obje:t moving rapidly through
the atmosphere and the buffeting is not distracting
nor does it interfere with pilot function.
The drogue parachute deployment is quite visible
from inside the spacecraft and the firing of drogue
parachute mortar is clearly audible. The opening
shock of the drogue paraciute is mild; there is a mild
pulsation or breathing of 1 he drogue parachute which
can be felt inside the spacecraft.
As the drogue parachute is released, the space-
craft starts to drop at a greater rate. The change
in g -field is quite notice able. Main parachute de-
ployment is visible out the window also. A mild
shock is felt as the main parachute deploys in its
reefed condition. The ccmplete parachute Is visible
at this time. As the reefing cutters fire, the para-
chute deploys to its fully opened condition. Again,
(al Normal stored position.
Figure 7-6.
a mild shock is felt. About 80 percent of the para-
chute is visible at this time and it is quite - n-
forting sight. The spacecraft rotates and ?
slowly under the parachute at first: the rate ^re
mild and hardly noticeable.
The spacecraft landing in the water was a mild
jolt; not hard enough to cause discomfort or dis-
orientation. The spacecraft recovery section went
under the water and I had the feeling that I was
on my left side and slightly head down. The w indow
was covered completely with water and there was
a disconcerting gurgling noise. A quick check
showed no water entering the spacecraft. The space-
craft started to slowly right itself: as soon as I was
sure the recovery section was out of the water, I
ejected the reserve parachute by actuating the re-
covey aids switch. The spacecraft then righted
itself rapidly.
I felt that I was in good condition at this point
and started to prepare myself for egress. I had
previously opened the face plate and had discon-
nected the visor seal hose while descending on the
main parachute. The next moves in order were to
disconnect the oxygen outlet hose at the helmet,
unfasten the helmet from the suit, release the chest
(b) Unrolled position.
Neck dam.
54
strap, release the lap belt and shoulder harness, re-
le?' Ki knee straps, disconnect the biomedical sen-
se 1 roll up the neck dam. The neck dam is
a ru. .jcr diaphragm that is fastened on the exterior
of the suit, below the helmet attaching ring. After
the helmet is disconnected, the neck dam is rolled
around the ring and up around the neck, similar
to a turtle-neck sweater. I See fig. 7-6. ) This left
me connected to the spacecraft at two points, the
oxygen inlet hose which I reeded for cooling and
the helmet communications lead.
At this time, I turned my attention to the door.
First, I released the restraining wires at both ends
arid tossed them towards my feet. Then I removed
the knife from the door and placed it in the sur-
vival pack. The next task was to remove the cover
and safety pin from the hatch detonator. I felt at
this time that everything had gone nearly perfectly
and that I would go ahead and mark the switch
position chart as had been requested.
After about 3 or 4 minutes, I instructed the heli-
copter to come on in and hook onto the spacecraft
and confirmed the egress procedures with him. I
unhooked my oxygen inlet hose and was lying on
the couch, waiting for the helicopter's call to blow
the hatch. I was lying flat on my back at this time
and I had turned my attention to the knife in the
sur--;"al pack, wondering if there might be some way
I carry it out with me as a souvenir. I heard
tl. tch blow — the noise was a dull thud — and
looked up to see blue sky out the hatch and water
start to spill over the doorsill. Just a few minutes
before, I had gone over egress procedures in my
mind and I reacted instinctively. I lifted the helmet
from my head and dropped it, reached for the right
side of the instrument panel, and pulled myself
through the hatch.
After I was in the water and away from the space-
craft, I noticed a line from the dyemarker can over
my shoulder. The spacecraft was obviously sinking
and I was concerned that I might be pulled down
with it. I freed myself from the line and noticed
that I was floating with mv shoulders above water.
The helicopter (fig. 7—7) was on top of the space-
craft at this time with all three of its landing gear
in the water. I thought the copilot was having dif-
ficulty hooking onto the spacecraft and I swam the
4 or 5 feet to give him some help. Actually, he had
cut the antennae and hooked the spacecraft in record
time.
The helicopter pulled up and away from me with
tb-~ -oacecraft and I saw the personal sling start
down; then the sling was pulled back into the
helicopter and it started to move away from me.
At this time, I knew that a second helicopter had
been assigned to pick me up, so I started to swim
away from the primary helicopter. I apparently got
caught in the rotorwash between the two helicopters
because I could not get close to the second helicopter,
even though I could see the copilot in the door with
a horsecollar swinging in the water. I finally
reached the horsecollar and by this time, I was get-
ting quite exhausted. When I first got into the
water, I was floating quite high up: I would say
rmr armpits were just about at the water level. But
the neck dam was not up tight and I had forgotten
to lock the oxvgen inlet port: so the air was gradu-
ally seeping out of my suit. Probably the most air
was going out around the neck dam, but I could see
that I was gradually sinking lower and lower in
the water and was having a difficult time staying
afloat. Before the copilot finally got the horse-
collar to me, I was going under water quite often.
The mild swells we were having were breaking over
my head and I was swallowing some salt water. As
I reached the horsecollar, I slipped into it and I
knew that I had it on backwards I fig. 7—8) ; but I
gave the "up ' signal and held on because I knew
that I wasn't likely to slip out of the sling. As soon
as I got into the helicopter, mv first thought was to
get on a life preserver so that if anything happened
to the helicopter, I wouldn't have another ordeal
in the water. Shortly after this time, the copilot
informed me that the spacecraft had been dropped
as a result of an engine malfunction in the primary
helicopter.
Postflight
The postflight medical examination onboard the
carrier was brief and without incident. The loss
of the spacecraft was a great blow to me. but I felt
that I had completed the flight and recoverv with
no ill effects.
The postflight medical debriefing at the Grand
Bahama Island installation was thorough and com-
plete. The demands on me were not unreasonable.
Conclusions
From the pilot's point of view the conclusions
reached from the second U.S. manned suborbital
flight are as follows:
ll) The manual proportional control system
functioned adequately on this flight. The system is
capable of controlling the retrofire accurately and
55
Fiuure 7 7. Helicopter hovering over spacecraft.
56
safely. The roll axis is underpowered and causes
so 'ifticultv. The rate command system func-
t erv well during this flight. All rates were
dai..,,».-d satisfactorily, and it is easy to hold and
maintain the attitudes with the rate command svs-
tem. If the rate of fuel consumption that was ex-
perienced on this flight is true in all cases, it would
not lie advisable to use the rate command system
during ordinary orbital flight to control attitudes.
It should he used only for retrofire and reentry. The
autopilot functioned properly with the possible ex-
ception of the 5 seconds of damping immediate!)
after separation. This period is so brief that it was
impossible to determine the extent of any damping.
The turnaround maneuver in the pitch and yaw axes
was approximately as predicted, but the roll axis was
>low to respond.
i2i The pilot's best friend on the orbital flight
is going to be the w indow. Out this window. 1 feel
he will he able to ascertain accurately his position at
all times. I ant sure he will be able to see stars on
the dark side and possibly on the daylight side, with
a little time to adapt the eves. The brighter stars
and planets will certainly be v isible.
( 3 i Spacecraft rates and oscillations are very" easy
to ascertain bv looking at the horizon and ground
checkpoints. 1 feel that drift rates will be easy to
distinguish on an orbital flight when there is time
to concentrate on specific points outside the window.
(4 I Sounds of pyrotechnics, control nozzles, and
control solenoids are one of the pilot s best cues as
to what is going on in the spacecraft and in the
sequencing. The sounds of posigrades. retrorockets.
and mortar firing are so prominent that these become
the primary cues that the event has occurred. The
spacecraft telelight panel becomes of secondary im-
portance and merely foiifirm- that a sequence has
happened on time. The sequence panel's main value
is telling the pilot when an event should have oc-
curred and has not.
loi Vibrations throughout the flight were of a
low order and were not disturbing. The buffeting at
maximum dynamic pressure and a Mach number of
1 on launch was mild and did not interfere with
FlCL'RE i-B. Helicopter recovering pilot i horserollar on backwards) .
pilot functions. Communications and vision were
satisfactory throughout this period. The mild buf-
feting on reentry does not interfere with any pilot
functions.
(6 I Communications throughout the flight were
satisfactory. Contact was maintained with some
facility at all times. There was never any require-
ment to repeat a transmission.
(7i During the flight, all spacecraft sys p-
peared to function properly. There was no 1 v,., fire-
men t to override any system. Every event occurred
on time and as planned.
Reference
1. Slaytox, Dotvald K. : Pilot Training and I'rejiight Preparation. Proc. Conf. on Results of the First U.S. Manned
Suborbital Space Fligh ■, NASA, Nat. Inst. Health, and Nat. Acad. Sri., June 6, 1961, j.p. 53-60.
Table 7-1. — Flight Plan
rime, Event
min:sec
0:01) Li ft -off
0:30 Svstems report
1:00 ; Svfrlems rejtorl
l:l."> Cabin, pressure report
1:30 Svstetiis report
2:00 Systems report
{Launch-vehicle engine cutoff
Ti over jet tison
Relrojeltison switch to OFF
2:33 Spacecraft separation from launch vehicle
2:38 Spacecraft turnaround to flight attitude
on autopilot
3:00 Transfer of flight control from autopilot
to manual proportional control system,
and evaluation of system
1:00 ; Spacecraft yawed to0 to left using horizon
I as attitude reference
.1:10 : Ketrograde rockets fired manuallv
Rrtrojettison svstem armed
Transfer of flight control from manual
>:3.> proportional control svstem to rate
command control system
Kadio transmitter switched from I HI'
to IIF
0:10 Rctropackage jettison
{Periscope retracts automatically
Spacecraft positioned into reentry alti-
tude
7:00 Communications switched hack lo L 11 F
I ransmit ler
7:46 Reentry starts
(Drogue parachute deploys
Snorkels open
Emergency rate oxygen flow
10:13 Main parachute deplovment
l.">:37 Landing
58
J. S GOVERN MF!nT PRIMING OFFICE ■ 1961